Distribution - Sandia National...
118
Transcript of Distribution - Sandia National...
..
.4
Iaaued by Sandiss National Laboratories. operated for the Ufited States Dep=tment ofEnergy by Sandia Corporation.
NOTICE: Tbia report was prepared ae an account of work sponsored by arr agency of theUnited States Government. Neither the United States Govemrnent nor anY agency thereof,nor any of their employees, nor anY of their contractors, aubcontracto~, or. thememployees, makes anY warranty, expreaa or implied or assumes anY legal fmbfity orresponaibiht y for the accuracy, completeness, or uaef~eas of an information, apparatus,product, or process disclosed, or represent? ,that its uss wo ~d not infringe privatelyowned rigbta. Reference herein to anY apeclfm commercmf product, Prpce~, or. serviceby trade name, trademark, menufact~er, or otherwise does not necesaamly constitute orIIISPIY Its endorsement, recomm:ndatlon, or favoring by tbe United States Government,any agency thereof or anY of them contractors or subcontractors. The wews and opinionsexpressed herein do not necessarily state or reflect those of the United StatesGovernment, any agency thereof or smy of their contractors or subcontractors.
Printed in the United States of AmericaAvailable from
National Technical Information ServiceU. S. Department of Commerce5285 Port Royal RoadSpringfield, VA 22161
NTIS price codesPrinted copy: $9.00Microfiche copy: AO1
,@
SAND80-2114Unlimited ReleasePrinted March 1981
DistributionCategory UC-60
Aerodynamic Characteristicsof Seven Symmetrical AirfoilSections Through 180-DegreeAngle of Attack for Use inAerodynamic Analysis ofVertical Axis Wind Turbines
Robert E. SheldahlAerothermodynarnics Division 5633andPaul C. KlimasAdvanced Energy Projects Division 4715Sandia National LaboratoriesAlbuquerque, NM 87185
ABSTRACTWhen work began on the Darrieus vertical axis wind turbine (VAWT) programat Sandia National Laboratories, it was recognized that there was a paucity ofsymmetrical airfoil data needed to describe the aerodynamics of turbine blades.Curved-bladed Darrieus turbines operate at local Reynolds numbers (Re) andangles of attack (a) seldom encountered in aeronautical applications. This reportdescribes (1) a wind tunnel test series conducted at moderate values of Re inwhich O < a ~ 180° force and moment data were obtained for four symmetricalblade-candidate airfoil sections (NACA-0009, -0012, -0012H, and -0015), and (2)how an airfoil property synthesizer code can be used to extend the measured ,properties to arbitrary values of Re (l@ = Re < 107) and to certain other sectionprofiles (NACA-0018, -0021, -0025).
ACKNOWLEDGMENTSB. F. Blackwell, Sandia National Laboratories Organization, 1537, was involvedwith the Sandia wind energy program when the experimental data for thisreport were obtained; his contributions to the program are gratefully acknowl-edged. The efforts of Professor M. H. Snyder and the personnel of the Walter H.Beech Memorial Low-Speed Wind Tunnel at Wichita State University, Wichita,Kansas, in obtaining the experimental airfoil section data and R. E. French,Sandia Organization, 5636, in producing the computed airfoil data are greatlyappreciated.
CONTENTSSYMBOLS .............................................................................. ....................... 8Introduction .............. .............................................. ..................................... 9Airfoil Section Models ......................................................... ...................... 9Test Facility .................................................................................................. 10Test E~escription ................................................... ........................................ 10Experimental Results .................................................................................. 10Reyncllds Number Extrapolation .............................................................. 11Conclusions ........................................................................ ..........................l2Refer(!nces ................................................................................................. .... 12
Tables1
2
3
4
5
6
Coordinates for the Modified NACA-0012 (NACA-0012H) Air-fctil . ..................................................... ................................................. 12
Lift and Drag Coefficients for the NACA-0012 Airfoil (104 s Re~ lo7) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ..oo. . ..o . . . . . . . . . . . ..r . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13
Lift and Drag Coefficients for the NACA-0015 Airfoil (104 s Re~ IOT)................................. ........................+.o.4...o.............o............. ..... 27
Lift and Drag Coefficients for the NACA-0018 Airfoil (104 s Re~ 5 x 106) . . . .. O. . . . . . . .. O.O...O.O. . .. O. . .. O. . . . . . ..4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. O...@... 41
Lift and Drag Coefficients for the NACA-0021 Airfoil (104 = Re<5 x 106)—. ............................. .................. ......................... ................... 52Lift and Drag Coefficients for the NACA-0025 Airfoil (104 ~ Re~ 5 x 106) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .. O.<. . . . . . . . . . . . . .. O. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63
IllustrationsFigure
1
2
3
4
5
6
7
8
9
10
Equatorial Plane Angle of Attack Variation for the 17-MetreTurbine at a Rotational Speed of 46 rpm (4.82 rad/s) ................. 75
Variation of the Chord Reynolds Number at the EquatorialPlane of the 17-Metre Turbine at a Rotational Speed of 46 rpm(4.82 rad/s) ......................................................................................... 76
%ction Lift Coefficients for the NACA-0009 Airfoil at ReynoldsNumbers of 0.36 x 106 and 0.69 x 106............................................. 77
Section Lift Coefficients for the NACA-0012 Airfoil at ReynoldsNumbers of 0.36 x 106 and 0.70 x 106....... ...................................... 78
%ction Lift Coefficients for the NACA-0012 Airfoil at ReynoldsNumbers of 0.86 x 10s and 1.76 x 106............................................. 79
Section Lift Coefficients for the NACA-0012H Airfoil at Rey-nolds Numbers of 0.36 x 106 and 0.70 x 106.... .............................. 80
%:ction Lift Coefficients for the NACA-0015 Airfoil at ReynoldsNumbers of 0.36 x 106 and 0.68 x 106........ .......................... ........... 81
Section Lift Coefficients for Four Airfoil Sections at an Approxi-mate Reynolds Number of 0.70 x 106............... .............................. 82
Full Range Section Lift Coefficients for the NACA-0009 Airfoilat Reynolds Numbers of 0.36 x 106, 0.50 x 106,and 0.69 xlOc ...................................................................................... 83
Full Range Section Lift Coefficients for the NACA-0012 Airfoilat Reynolds Numbers of 0.36 x 106, 0.50 x 106,and 0.70 x 10c ............................................................... ...................... 84
Illustrations (Cent)Figure
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
Full Range Section Lift Coefficients for the NACA-0012H Air-foil at Reynolds Numbers of 0.36 x 106, 0.49 x 106,and 0.70 x 106 .......................................................................... ........... 85Full Range Section Lift Coefficients for the NACA-0015 Airfoilat Reynolds Numbers of 0.36 x 106, 0.50 x 106, and0.68 X 106... . .. . ....................................... ................................. ............. 86Section Drag Coefficients for the NACA-0009 Airfoil at SmallAngles of Attack and Reynolds Numbers of 0.36 x 106, 0.50x 106,and 0.69 x 106 .................................................................... ................. 87Section Drag Coefficients for the NACA-0012 Airfoil at SmallAngles of Attack and Reynolds Numbers of 0.36 x 106, 0.50x 106,and 0.70 x 106 ...................................................................... ............ 88Section Drag Coefficients for the NACA-0012 Airfoil at SmallAngles of Attack and Reynolds Numbers of 0.86 x 106, 1.36x 106,and 1.76 x 106. ....................................... ............................................. 89Section Drag Coefficients for the NACA-0012H Airfoil at SmallAngles of Attack and Reynolds Numbers of 0.36 x 10fI, 0.49 x10A,and 0.70 x 10b.............................. ................................................. 90
Section Drag Coefficients for the NACA-0015 Airfoil at SmallAngles of Attack and Reynolds Numbers of 0.36 x 10fI, 0.50x 106,and 0.68 x 106 ..... ............... .................................... ............................. 91Full Range Section Drag Coefficients for the NACA-0009 Airfoilat Reynolds Numbers of 0.36 x 106, 0.50 x 106,and 0.69 x 106... ............................................. ............................ ......... 92Full Range Section Drag Coefficients for the NACA-0012 Airfoilat Reynolds Numbers of 0.36 x 106, 0.50 x 106, and0.70 X 106 ... ........................ ................... ................. .............................. 93Full Range Section Drag Coefficients for the NACA-0012HAirfoil at Reynolds Numbers of 0,36 x 106, 0.49 x 106, and0.70 X 106................ .................. ......................................................... 94Full Range Section Drag Coefficients for the NACA-0015 Airfoilat Reynolds Numbers of 0.36 x 106, 0.50 x 106,and 0.68 x 106 ............. .................................... .................................... 95NACA-0009 Airfoil Section Moment Coefficients About theQuarter Chord for Reynolds Numbers of 0.36x 106, 0.5x 106 and0.69 X 106............................ .............................................. ................. 96NACA-0012 Airfoil Section Moment Coefficients About theQuarter Chord for Reynolds Numbers of 0.36 x 106, 0.50 x 106,and 0.70 x 106 .................................................................... ................. 97NACA-0012 Airfoil Section Moment Coefficients About theQuarter Chord for Reynolds Numbers of 0.86 x 106, 1.36 x 106,and 1.76 x 10fI... ... ............................ .................. ....................... .......... 98NACA-0012H Airfoil Section Moment Coefficients About theQuarter Chord for Reynolds Numbers of 0.36 x 106, 0.49 x 106,and 0.70 x 10fJ............................ ................................................... ..... 99NACA-0015 Airfoil Section Moment Coefficients About theQuarter Chord for Reynolds Numbers of 0.36 x 106, 0.50 x 106,and 0.68 x 106 .~..... ..... ........................................................... ............. 100
6
Illustrations (Cent)Figure
27
28
29
30
31
32
33
34
35
36
37
Full Range Section Moment Coefficients About the QuarterChord for the NACA-0009 Airfoil at Reynolds Numbers of 0.36 x106, (3.50 x 106, and 0.69 x 1(36 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 101
Full Range Section Moment Coefficients About the QuarterChord for the NACA-0012 Airfoil at Reynolds Numbers of 0.36 x106, 0.50 x 106 and 0.7(3 x 1(36 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 102
Full Range Section Moment Coefficients About the QuarterChord for the NACA-0012H Airfoil at Reynolds Numbers of0.36 x 106, 0.49 x 106, and 0.70 x 10s .......................... ..................... 103
Full Range Section Moment Coefficients About the QuarterChord for a NACA-0015 Airfoil at Reynolds Numbers of 0.36 x106, 0.50 x 10s, and 0.68 x 10b.................. ......................... ................ 104
Full Range Section Axial Force Coefficients for the NACA-0012Airfoil at Reynolds Numbers of 0.36 x 106, 0.50 x 106and 0.70 x 10s .. ................................................................................... 105
Full Range Section Axial Force Coefficients for the NACA-0012H Airfoil at Reynolds Numbers of 0.36 x 106, 0.49x 106 and0.70 X 10s .......................................................................... ................... 106
Full Range Section Axial Force Coefficients for the NACA-0015Airfoil at Reynolds Numbers of 0.36 x 10s, 0.50 x 106and 0.68 x 10s ................................... .................. ................................ 107
Predicted and Measured Values of Minimum Section DragCoefficients, Cdo, as a Function of Reynolds number, Re ............108
Predicted and Measured Values of Section Maximum Lift Coef-ficients, C~~u, as a Function of Reynolds number, Re ................109
Power Coefficient as a Function of Tip-Speed Ratio for theSandia 17-m Diameter Darrieus Turbine with a Height to Diam-eter Ratio of 1.0, Two NACA-0015 0.61-m Chord Blades at aRotational Speed of 50.6 rpm . ....... .................................................. 110
Power Coefficient as a Function of Tip-speed Ratio for theSandia 5-m Diameter Darrieus Turbine with a Height to Diame-ter Ratio of 1.0, Two NACA-0015 O.15-m Chord Blades at aRotational Speed of 162.5 rpm . ....................................................... 111
7
SYMBOLS4c
Ca
cd
c!
cm
Cp
Q%R
Re
u
Vm
x
a
8
l.%)
Pa
@
Turbine swept area
Airfoil chord length
Section axial force coefficient, axial force per unit span/q~c
Section drag coefficient, section drag per unit span/q~c
Section lift coefficient, section lift per unit span/q@c
Section moment coefficient, section moment at c/4 per unitspan /q~cz
Power coefficient,Qu
‘hpmVm3A~
Turbine Aerodynamic torque
Dynamic pressure, 1hpmVm2
Rotor radius
pmucReynolds numbers, —
1’%
Relative velocity
Free stream wind velocity
Tip speed ratio, &m
Angle of attack
Angle of rotation about the turbine vertical axis
Free stream viscosity
Free stream density
Turbine angular velocity
Aerodynamic Characteristicsof Seven Symmetrical AirfoilSections Through 180-DegreeAngle of Attack for Use inAerodynamic Analysis ofVertical Axis Wind Turbines
IntroductionWhen analytical work began on the vertical axis
wind turbine, it immediately became apparent thatavailable data for symmetrical airfoil sections waslimited. The section data requirements for applica-tion to vertical axis wind turbines are broader inscope than are those the aircraft industry usuallyconcerns itself with. Figure 1 shows the range ofangle of attack the airfoil at the equatorial plane of aDarrieus turbine is exposed to for various tip speedratios. At low tip speed ratios, it is possible to be at anangle of attack approaching 180 deg. In operation,with a tip speed ratio in excess of 2.0, the angle ofattack can exceed 25 deg. Portions of the airfoil closerto the axis of rotation will see even greater angles ofattack. This figure shows only one-half of the revolu-tion; the second half will be similar except the anglesof attack will be negative. Thus the airfoil is subjectedto a continually changing angle of attack cyclingfrom positive to negative back to positive as it re-volves about the vertical axis. This particular figure isfor the 17-m turbine but results are similar for tur-bines of all sizes. The requirements here call forsection data for angles of attack to 180 deg and datafor both increasing and decreasing angle of attackshowing airfoil hysteresis.
The turbine blade changes its angle of attack as itmakes its orbit about the rotational axis, The localReynolds number changes also. In Figure 2, theReynolds number is shown as a function of therotation angle for several tip speed ratios. Again, thisis for the 17-m system at a fixed rotational speed of 46rpm (4.82 :rad/see) and a blade chord of approximate-ly 0.5 m. When the turbine operates with a tip speedratio in excess of 2.0, the Reynolds number range isfrom 0.5 x 106 to 2 x 106. Scaled down turbines willalso have lower Reynolds numbers proportional tochord length. A Sandia 2-m wind tunnel model oper-ated over a range of Reynolds numbers from 0.1 x 106
to 0.3 x 106 in a recent wind tunnel test. The require-ments here call for section data over a wide Reynoldsnumber range. Data for the low Reynolds numbers(less than 0.5 x 10s) are needed to compare the solu-tions from computer models with the data from windtunnel model tests.
These requirements are generally out of the rangeof most published airfoil section data. Examples ofpublished data for symmetrical airfoil sections arepresented in Refs 1 and 2. The NACA-0012 is one ofthe more popular symmetrical airfoils because of itsfavorable lift to drag ratio, so there are more dataavailable for that airfoil.
Sandia National Laboratories contracted withWichita State University to construct four differentsymmetrical airfoil sections and to test the models atangles of attack to 180 deg for three different Reyn-olds numbers. We selected the lowest Reynolds num-ber obtainable that would still be within the oper-ational range of its facility and balance system. Thepurpose of these tests was to obtain needed sectiondata for the NACA-0009, -0012, and -0015 airfoilsover the angle of attack range of interest at as low aReynolds number as possible. Also,airfoil, a modified-OO12 designatedwas tested.
Airfoil Section Models
a nonstandardNACA-0012H,
Four symmetrical airfoil models were constructedof aluminum; a fifth model was constructed of woodto standard wind tunnel model tolerances by WichitaState University. All the aluminum models had 6-in.(15.24-cm) chords with a 3-ft (0.91-m) span. Three ofthese models (NACA-009, -0012, and -0015) had stan-dard airfoil cross sections; geometries for these air-foils are found in Ref 3. The fourth model was anonstandard airfoil. It was a modification of the
9
NACA-O012 provided by Raymond M. Hicks of NA-SA/Ames Research Center.i The modification wasdesigned with the aid of a computer program toincrease the c~~= of a given airfoil by reducing theleading edge pressure spike associated with subsonicairfoils. The new airfoil has been designated NACA-0012H because its thickness to chord ratio was leftunchanged at 12?10.The geometry for this airfoil ispresented in Table 1. The fifth airfoil model had a 15-in. chord (38. 10-cm) with a 3-ft (0.91-m) span and alsohad an NACA-0012 cross section. This model wasconstructed to obtain airfoil data at higher Reynoldsnumbers and could not, because of its size, be testedat an angle of attack greater than 30 deg.
Test FacilityThe airfoils were tested in the Walter H. Beech
Memorial Wind Tunnel at Wichita State University.sThe Tunnel has a 7 x 10-ft (2.13x 3.05 m) test sectionfitted with floor to ceiling two-dimensional insertsfor testing two-dimensional airfoil sections. Theseinserts in the center of the test section act as flowsplitters to form a separate test section 3 ft (0.91 m)wide by 7 ft (2.13 m) tall. Part of the total airflow inthe wind tunnel passes through the 3 x 7 ft sectionand part passes by each side. The 3 x 7 ft section isseparately instrumented with pitot-static probes fordetermining flow conditions within that section. Awake survey probe was installed in the wind tunnelon a separate series of tests to obtain the airfoilsection drag at low angles of attack for all airfoilmodels.
Test DescriptionThe airfoil mod~ls were attached to the end plates
in the walls of the two-dimensional inserts. Theseend plates are the attachments to the angle-of-attackcontrol mechanism and the facility balance system.The aluminum models were tested at nominal Rey-nolds numbers of 0.35 x 106, 0.50 x 106 and 0.70 x 106through angles of attack of 180 deg. The angle-of-attack control mechanism has an approximate rangeof 60 deg; this required that the model be reorientedon the end plates three times to complete the fullrange of angles of attack to 180 deg. This allowed forsome overlap of data near 40,90, and 130 deg. The 15-in. chord model was tested at Reynolds numbers of0.86 x 106, 1.36x 106 and 1.76 x 106 through angles ofattack of -20 to +30 deg.
Data for each airfoil were first obtained over therange of -24 to +32 deg (increasing a) and then from+32 deg to -24 deg (decreasing a) for the threeReynolds numbers. The 15-in. chord model was limit-ed to a range of -20 to +30 deg. This was done to
obtain the hysteresis loop in the region of airfoil stall.All full range data were obtained with increasingangles of attack to 180 deg. Lift, drag, and momentdata were obtained from the balance system. All thedata were corrected for wake and solid blockage,bouyancy, upwash, and wind-turbulence factor.b Theturbulence factors used to correct the Reynolds num-bers to 0.35x 106, 0.50x 106, and 0.70x 106 were 1.38,1.29, and 1.13, respectively. All of the tests reported ‘here were performed on aerodynamically smoothairfoils. A separate test of the NACA-0015 airfoil with .transition strips was conducted; the strips were of No.80 Carborundum grit glued to a strip approximatelyO.l-in. (0.25-cm) wide located approximately at 17%of chord station. The results with the strips weresimilar to the results without them and thus wereinconclusive and are not presented here.
Experimental ResultsThe section coefficient of lift data for the four 6-
in. chord airfoils and the 15-in. airfoil are shown inFigures 3 through 7 for the angles of attack from -24to +24 degrees at nominal Reynolds numbers of 0.35x 106 and 0.70x 106 for the 6-in. chord airfoils and 0.86x 106 and 1.76 x 106 for the wooden 15-in. chordairfoil. Each airfoil cross section is sketched in thefigures. These figures include data obtained for bothincreasing and decreasing angle of attack; they dem-onstrate the extent of the lift coefficient hysteresis foreach airfoil. The lift coefficient for the NACA-0009airfoil shown in Figure 3 reaches a maximum ofapproximately 0.8 near 10-deg angle of attack. Thereis not a significant drop in lift past stall nor is thereany significant hysteresis. Data for the NACA-0012are shown in Figure 4; we see that Ctm has increased
to 1.0 for positive angles and to -1.08 for negativeangles with a hysteresis loop most pronounced fornegative angles. The lift coefficient data for thewooden NACA-0012 airfoil at Reynolds numbers of0.86 x 106 and 1.76 x 106 are shown in Figure 5; here,the anticipated improved Ctm= at the larger Reynolds
numbers can be seen.The NACA-0012H lift data are presented in Fig-
ure 6 and show dramatic improvement in lift charac-teristics over the NACA-0012 for similar Reynoldsnumbers. The maximum lift coefficient approachest 1.2 at the higher Reynolds number condition. Notethe larger size of the hysteresis in the lift data nearpositive and negative stall angles. The dashed line inthe figure shows the curvature of the standardNACA-0012 airfoil. The lift data for the NACA-0015(Figure 7)are similar to the NACA-0012H. The maxi-mum lift coefficient for the -0015 is slightly less than
‘
10
that for the -O012H, but stall is less abrupt and occursat a slightly greater angle of attack. Figure 8 is acomposite of the data for the four 6-in. chord airfoilsand shows lift data at a Reynolds number of 0.7 x 106.Data shown are for increasing angle of attack forpositive angles and decreasing angle of attack fornegative angles; this shows the increased perfor-mance of the NACA-0012H and the favorable perfor-mance of the NACA-0015.
Figures 9 through 12 show the full range sectionlift coefficient data for the four small airfoils. All datawere taken with the angle of attack increasing. Thedata for all the airfoils beyond 25-deg angle of attackare similar. At an angle of 40 to 45 deg, the liftcoefficient for a -0009 airfoil is greater than 1.1; withincreasing airfoil thickness, the lift coefficient de-creases to 1.05 but, generally speaking, the effect ofthe Reynolds number (in the range of 0.35 x 106 to0.70 x 106) and the airfoil geometry have little effecton the 1ift coefficient in the angle of attack range of25 to 181Ddeg.
The section drag coefficients for the airfoils areshown in Figures 13 through 17 over the angle-of-attack range of -16 to +16 deg. The minimum dragcoefficient near zero lift is approximately 0.006 forthe NACA-0009. The data for the drag coefficientswere obtained by the balance system and were cor-rected by data obtained in the angle-of-attack rangeof positive to negative stall by a wake survey meth-od.4 This corrected the force data for drag on the endplates. The full range section drag coefficients for thefour small airfoil sections are shown in Figures 18through 21. These data are similar for all anglesgreater than 20 deg. At 90 deg, the drag coefficient ofapproximately 1.8 is near Hoerner’s value of 1.98 for atwo-dimensional flat plate.T
For completeness, the airfoil section moment co-efficients for the tested airfoils are included here.Shown in Figures 22 through 26 are the sectionquarter chord moment coefficients of each airfoil forthe angle-of-attack range from -24 to +24 deg forboth increasing and decreasing angles of attack. Theeffect of hysteresis on the moment coefficients in theregion c~faerodynamic stall can be clearly seen. Themoment coefficients are very near zero at small an-gles of attack (before airfoil stall) as is anticipated fora symmetrical airfoil. In Figures 27 through 30 are thefull range section moment coefficients about thequarter chord for the four airfoils with 6-in. chords atnominal. Reynolds numbers of 0.36 x 106, 0.50 x 106and 0.7CI x 106. There is a great deal of scatter in thedata for angles of attack greater than 45 deg and lessthan 135 deg. The full range moment coefficients arevery similar for all four airfoils.
The component of force that makes a vertical axiswind turbine work is the chordwise or axial force. Itis desirable to increase the area under the positiveportion of the curve for both positive and negativeangles of attack and to minimize the negative axialforce coefficients near zero angle of attack. Figures 31through 33 show the full range axial force coeffi-cients for the NACA-0012, -O012H, and -0015 airfoilsections. The important thing to note is the largerarea under the curve before airfoil stall for the-O012H and -0015 when compared to the -0012. Thisshould provide better performance from a wind tur-bine, using either one of these, than the NACA-0012airfoil. Note that the axial force coefficient is ob-tained by
c,=c, sina-c~cosff.
Data obtained in this manner beyond 20 deg becomevery scattered because the results are obtained bytaking small differences of larger numbers.
Reynolds Number ExtrapolationSection data at Reynolds numbers not tested, es-
pecially lower values, are needed to perform VAWTaerodynamic analyses with accuracy. The need alsoarises to consider blades whose airfoil sections are notincluded among the four profiles examined in thewind tunnel entry described above. These require-ments may be met by combining section propertypredictions from one of the currently available sec-tion synthesizer computer codes and those propertiesmeasured. Tables 2 through 6 list c~ and cd vs ainformation for O ~ a < 180° at Reynolds numbersbetween 104 and 107 obtained by such a combination.Pre- and early stall section information was calculat-ed, using the computer code PROFILE.S Late andpost-stall section characteristics were taken from themeasurements detailed above. Figures 34 and 35 com-pare calculated and measured zero lift drag coeffi-cients and maximum lift coefficient, respectively, forthe NACA 0015 airfoil. Agreement was consideredclose enough to justify the use of PROFILE predic-tions over the linear and early nonlinear portions ofthe c1 -a curve. For other values of a, it was seen thatbehavior was sufficiently independent of the Rey-nolds number to use the Wichita State Universitydata at all values of Re for which section informationwas sought. The precise angle of attack where thetables switched from calculated to measured perfor-mance coefficients was determined by trial and error.The criterion used was that the VAWT performance
11
as calculated by the conservation of momentum-based model DARTER9 using the hybrid airfoil char-acteristics most closely matched that obtained in fieldtests of the Sandia 17-m height-to-diameter (H/D) =1, two-bladed turbine with blades of NACA 0015section. The final comparison, using Table 3 (0015)information, is shown in Figure 36 for a turbineangular velocity of 50.6 rpm. The same crossoverpoint was then used in creating Tables 2, 4, 5, and 6(0012, 0018,0021, and 0025) data combinations. Notethat the tabulations for the 18%, 21%, and 25% thicksections relied upon Reynolds number independenceat high values of a.
Since Tables 2 through 4 were written, a next-generation class of aerodynamic loads/performancemodels has come into use at Sandia National Labora-tories. These are vortex /lifting line models and aredescribed in Ref 10. Figures 36 and 37 compare pre-dicted and measured performance for the Sandia 17-m and 5-m turbines (H/D = 1). These comparisonswould appear to further validate the hybridizingscheme used.
ConclusionsThe aerodynamic section data for four different
symmetrical airfoil cross sections (NACA-0009, -0012,-O012H, and -0015) were obtained for angles of attackup to 180 deg at nominal Reynolds numbers of 0.36 x106, 0.50 x 106 and 0.70 x 106. In addition, experimen-tal section coefficients were obtained for the NACA-0012 airfoil with a larger chord length at Reynoldsnumbers up to 1.76 x 106. The data were obtained for
Table 1. Coordinates for(NACA-0012H) AirfoilXlc
0.00.0050.0100.020
0.0300.040
0.0500.0600,080
0.1000.1250.1500.1750.2000.2250.250
*y/c
0.00.014380.020740.029250.035220.039820.043510.046550.051210.054540.057400.059240.060330.060870.061000.06084
use with vertical axis wind turbines performanceprediction computer codes. We extended the data to awider Reynolds number range (from 104 to 107) andexpanded to additional symmetrical airfoils (NACA-0018,-0021, and -0025) by the use of an airfoil sectioncharacteristics synthesizer computer code. These air-foil characteristics as used by the vertical axis windturbine performance prediction codes appear to be _adequately predicting VAWT performance.
*
References1.
2.
3.
4.
5.
6.
7.
8,
9,
10
E. N. Jacobs and A. Sherman, Air/oil Section Characteristics asA//ected by Variations OJ the Reynolds Number, NACA ReportNo. 586, 1937.
L. Loftin, Jr., and H. A. Smith, Aerodynamic Characteristics of 15NACA Airfoil Sections at Seven Reynolds Numbers from 0.7x 106to 9.0 x 106, NACA TN 1945, October 1949.
1, H. Abbott and A, E. Von Doenhoff, Theory of Wing Sections,(New York: McGraw-Hill Book Co, Inc, 1949).
PrivateCommunication, R. M. Hicks, NASA,AmesResearchCen-ter, Moffett Field, CA, 94035.
Information jor Users of the Walter H. Beech Memorial Low-SpeedWind ‘J’unne[, Wichita State University Aeronautical Engineer-ing Department, July 1966.
A. Pope and J. J. Harper, Low-Speed Wind Tunnel Testing, (NewYork: John Wiley & Sons, Inc, 1966).
S. F. Hoerner, Fluid Dynamic Drag, Midland Park, New Jersey,07432, 1965.
R. Eppler, “Turbulent Airfoils for General Aviation,” Journal ofAircraft, 15 (2): 93-99 (February 1978).
P. C. Klimas and R. E. French, A Users Manual for the VerticalAxis Wind Turbine Performance Code DARTER, SAND80-I 155(Albuquerque: Sandia National Laboratories, May 1980).
1. H. Strickland, B. T. Webster, T. Nmven, “A Vortex Model of.— .,.the Darrieus Turbine: An Analytical and Experimental Study:Journal o) Fluids Engineering, Vol. 101, No. 4, 1979.
the Modified NACA-0012
Xlc *ylc
0.275 0.060480.299 0.060020.349 0.059510.399 0.058080.449 0.055880.500 0.052940.550 0.049520.600 0.045630.650 0.041330.700 0,036640.750 0.031600.800 0.026230.850 0.020530.900 0.014480.950 0.008071.000 0.00126
12
Table 2. Lift and Drag Coefficients for the NACA-0012 Airfoil (104 s Re s 107
Re
10000.0 NACA 0012 SECTION DATA? EPPLER MOOELt CL? CD* DCC78
acd
o 0.0000 000000 .0337
0 100000 .0830 .0338
0 2.0000 ● 1534 ●0343
o 3.0000 .2009 .03510 4.0000 .2003 .035’30 5.0000 .0328 .0351
0 6.0000 -01413 ●0460
o 7.0000 -.1142 .0580
0 8.0000 -*0703 .07200 900000 -.0215 .08600 11000000 .0311 ●101Oo :11.0000 .0848 .1170
0 1200000 .1387 .13400 113.0000 .1928 .1520
:14000000 .2468 ●171Oo :15.0000 .3008 .19000 116.0000 .3548 .21000 1700000 .4079 .23100 ;1800000 .4606 .25200 1900000 .5121 .2740
0 :ZO*OOOO .5838 .2973T-koooo ●6161 .3200
0 :~z.000o” .6687 .34400 2300000 .7216 .3690
0 :~~.()()oo ●7744 .3940
0 25.0000 .8276 .4200
0 ;26.0000 .8810 .4460
0 2700000 .93+5 .4730
0 30.0000 .9150 .57(IO
o :35.0000 1.0200 .7450
0 40.0000 1.0750 .9200
0 4500000 1.0850 1.0750
0 !5000000 1.0400 1.2150
0 55.0000 .9650 1.3450
0 6000000 .8750 1.47000 65*0000 .7650 1.5750
0 70*0000 .6500 1.6650
0 75.0000 .5150 1073500 {3000000 .3700 1.78000 {3500000 .2200 1.8000
0 9000000 .0700 1.80000 9500000 -.0700 1.78000 100*OOOO -.2200 1.7500
0 105.0000 -.3700 107000
0 1:10.0000 -.5100 10635O0 1:15.0000 -e6250 1.55500 1:20.0000 -.7350 1.4650
13
Table 2. (cent)
O 125.0000 -.8400 1035000 130.0000 -*91OO 1.2250
0 13500000 -.9450 1.08500 140.0000 -09450 .9250
0 145.0000 -09100 .7550
0 150.0000 -.8500 .5750
0 15500000 -.7400 .4200
0 160.0000 -.6600 .3200
0 165.0000 -.6750 .23000 170.0000 -.8500 .1400
0 175.0000 -.6900 .0550
1 180.0000 0.0000 .0250
20000.0 NACA 0012 SECTION DATAs EPPLER MODELS C.S CDt DEC78
o 0.0000 0.0000 .0245
0 1.0000 ●1057 .02470 2.0000 .2072 .0251
0 3.0000 .3032 .0259
0 4.0000 .3929 .02700 5.0000 .4781 .0282
0 6.0000 -.0298 .0460-o 7.0000 -.1089 .0580
0 8-0000 -.0699 .07200 9.0000 --0198 .0860
0 10*OOOO .0320 .10100 11.0000 .0856 .1170
0 1200000 .1894 .1340
0 13.0000 .1934 .1520
0 14.0000 .2474 .1710
0 15.0000 .3014 ●191O
o 1600000 * 3554 .21000 17.0000 .4089 .23000 18.0000 .4620 .25200 19.0000 ●5147 .2740
0 2000000 .5663 .29700 21.0000 .6184 .3200
0 22.0000 .6709 .34400$ 23.0000 .7238 .3690
0 24.0000 .7765 .39400 25.0000 .8297 .4200
0 2500000 .8831 .44600 27.0000 .9365 .4730
0 3000000 .9150 .57000 35.0000 1.0200 .74500 40.000!) 190750 .92000 45.0000 1.3850 1.07500 50.0000 1.0400 1.21500 55.0000 .9650 1.345(I
o 60-0000 ●8750 1.47000 65-0000 ●7650 1.57500 70.0000 ●6500 1-6650—
.
.
,
14
Table !!. (cent)
o 75.0000 .51!50 1.7350
0 8000000 .3700 1078OO
0 85-0000 .2200 1-80000 90.0000 .0700 1-8000
0 95.0000 -.0700 1-7800
0 100.0000 -.2200 1.7500
0 105* OOOO -.3700 1.7000
0 110.0000 -*51OO 10635O
0 115.0000 -.6250 1.5550
0 12000000 -.7350 1s4650
O 125.0000 -.8400 1.3500
0 130.0000 -.9100 10225O
0 135.0000 -.9450 1.0850
0 140.0000 -.3450 .9250
0 14500000 -.9100 .7550
0 15000000 --8500 .5750
0 155.0000 -.7400 -4200
0 16000000 -s6600 .32000 16500000 -.6750 ●2300o 170.0000 -.8!500 .1400
0 17500000 -.6900 .05501 180s0000 0.0000 .0250
40000.0 NACA 0012 SECTION DATA? :PPLER I’403ELs CL? CD? DEC78o 0.0000 000000 .0175
0 1.0000 ●11OO .0177
0 2.0000 .2200 ●O181
o 3.0000 ●3376 .0189
0 4.0000 *4464 .0199
0 5.0000 ●5276 .0218
0 600000 -6115 .0232
0 7.0000 -.0212 .0580
0 8.0000 -.0615 .0720
0 9.0000 -00160 .0860
0 10.0000 .0344 *101O
o 11.0000 .0869 .1170
0 12.0000 ●1406 .1340
0 13.0000 ●1945 ●152~
o 14.0000 ●2484 ●171Oo 15.0000 ●3024 .1’3000 16.0000 -3563 ●21OOo 17.0000 ●4107 -2310
0 18-0000 ● 4644 ●2520
o 19.0000 .5178 -2740
0 20.0000 ,5708 ●2970o 21.0000 ●6232 .3200
0 22.0000 .6755 .3440
0 23-0000 ●7283 ●3690
o 24.0000 .7809 .3940
0 25.0000 .8340 .4200
0 26.0000 ●8873 .4450
15
Table 2. (cent)
–o 27-0000 ● 9407- ●473O
0 30.0000 .9150 .57000 35.0000 100200 .7450
0 4000000 1.0750 -92000 45.0000 1.0850 1.07500 50.0000 1.0400 1s2150o 55.0000 ● 9650 1.34500 6000000 ●3 750 1.47000 65.0000 .7650 1.57500 70.0000 ●6500 10665O0 75.0000 ●5150 1.73500 8000000 .3700 1078OO0 85s0000 .2200 1.80000 90.0000 .0700 1080000 95.0000 -.0700 1078OO0 10000000 -.2200 1.75000 105.0000 -.3700 1.70000 11000000 -*51OO 1s6350o 115.0000 --6250 1055500 120.0000 -.7350 1.46500 125s0000 --8400 1.,35000 130.0000 -.9100 1-22500 135.0000 -.9450 1,08500 140.0000 -.9450 -92500 145.0000 -.9100 .75500 150.0000 -.8500 .57500 15500000 -.7400 .4200
0 160-0000 --6600 .3200
0 16500000 -*6750 ●2300o 170.0000 -.8500 .14000 17500000 -s6900 .05501 18000000 0.0000 .02!50
80000-0 NACA 0012 SECTION DATAs EPPLER M03ELt CLt Co? DEC78o 0.0000 0.0000 .0133
0 1.0000 .1100 .01340 2.0000 .2200 ●0138o 3.0000 .3300 .01450 4.0000 .4400 .01550 500000 .5500 .01700 6-0000 ●6384 .01890 7.0000 ● 7227 -02040 8-0000 .6930 .02220 990000 -*OO1O ●0600o 10.0000 .0413 *0600o 11.0000 .0911 .11700 12.0000 .1430 .13400 1300000 ●1966 .15200 14.0000 .2504 ●171Oo 15.0000 .3043 .19000 15.0000 ● 3582 .2100
.
.
,
16
Table 2. (cent)
-——..—o 17.0000 .“4139 ●2310O 1800000 ●4689 .2520
0 19.0000 ●5232 .27400 20.0000 .5770 .29700 21.0000 ●6305 ●3200o 22.0000 m6839 .34400 2300000 ●7373 .36900 2400000 ● 7902 .39400 25.0000 ●8432 .4200
0 25.0000 ●8963 .4+60
O 27-0000 ●9496 .47300 3000000 ●9150 .57000 35.0000 100200 .7450
0 40.0000 1.0750 .9200
0 45.0000 1.0850 1.0750
0 5000000 100400 10215O0 55.0000 ●9650 1.34500 6000000 .8750 1.47000 6500000 .7650 1.5750
0 70.0000 .6500 1.66500 75.0000 .5150 1*735CIO 80.0000 .3700 1.78000 85.0000 .2200 1.8000
0 9000000 .0700 1080000 95.0000 -.0700 1-78000 100.0000 -.2200 1.7500
0 105* OOOO -.3700 1.7000
0 110.0000 -.5100 1.6350
0 115.0000 -.6250 1.55500 1,20.0000 -.7350 10465O0 125.0000 -08400 1.35000 130.0000 -.9100 102250
0 135.0000 -.9450 1.0850
0 140.0000 -.9450 .9250
0 145.0000 -.3100 .7550
0 150.0000 -m8500 .5750
0 155.0000 -.7400 .4200
0 160,0000 -.6600 s3200
O 165.0000 --6750 ●2300o 170.0000 -m8500 .14000 175.0000 --6900 ●05501 18000000 0.0000 -0250
160000.0 NACA 0012 SECTION DATA* EPPLER MO)EL? C-s CDS 0EC78o 0.0000 000000 .0103
0 1.0000 .1100 .0104
0 2.0000 ●2200 -0108
0 3.0000 .3300 .0114
0 4.0000 .4400 .0124
0 5.0000 .5500 .0140
0 5*0000 s6600 -0152
17
Table 2. (cent)
_ —-0 7.0000 .7460 .01700 8.0000 .8274 .01850 9.0000 .8527 .02030 10.0000 .1325 -01880 11.0000 ●1095 .07600 12.0000 ●1533 .13400 13.0000 ●2030 -15200 14.0000 .2546 .17100 1500000 .3082 .19000 1600000 ,3620 .21000 1700000 *4200 .23100 18.0000 .4768 .2520
0 1900000 ●5322 -27400 20.0000 *5870 -29700 21.0000 .6414 .32000 22.0000 .6956 .34400 23.0000 .7497 .36900 2400000 ●8034 .39400 25.0000 .8572 ●4200o 26.0000 ●9109 ●4450o 27s0000 .9646 .4730
0 30.0000 .9150 .57000 35.0000 1.0200 .74!50
o 40.0000 1.0750 .92000 45.0000 1.0850 1.0750
0 50.0000 1.0400 1.21500 55.0000 ●9650 1.3450
0 60.0000 ●3750 1047000 65.0000 .7650 1.5750
0 70.0000 S500 1.66500 75.0000 .5150 1.73500 80.0000 .3700 1.78000 85.0000 .2200 1.80000 90.0000 .0700 108000
0 95.0000 -.0700 1-7800
Q 10000000 -.220rJ 1075000 105.0000 -*3700 1.7000
0 110.0000 -*5100 1.5350
0 115.00C0 --6250 1.55500 120.0000 -.7350 1.46500 125.0000 -.8400 1.3500
o 130.0000 -.9100 1022500 135.0000 -.9450 1.0850
0 140.0000 -.9450 .92500 145.0000 -.9100 .75500 15000000 -08300 .57500 155.0000 -.7400 -4200
.
‘
*
O 160.0000 -.6600 .32000 165.0000 -.6750 .23000 170.0000 -.8500 .1400
18
Table 2. (cent)
o 175.0000 --6900 .0550
1 180.0000 000000 ●0250
360000.0 NACA 0012 SECTION DATA? EPPLER M03EL~ CL? C!3S DEC78
o 0.0000 0.0000 .00790 100000 .1100 ●0080o 2.0000 .2200 -00840 300000 .3300 .00890 4.0000 .4400 ●0098o 5.0000 .5500 .01130 6.0000 .6600 ●0125o 7.0000 .7’700 .01350 800000 .8542 .01550 9.0000 ●9352 ●0167o 10.0000 ●9811 .01840 11.0000 -9132 .02040 12.0000 ●4832 ●0217o 13.0000 ● 2759 .02220 1400000 ●2893 -1060
0 15.0000 .3306 .19000 15.0000 ,3792 ●21OOo 17.0000 ● 4455 ●231Oo 18.0000 ●5047 .25200 13.0000 ●5591 .27400 20.0000 .6120 .29700 21.0000 ,6643 .32000 22.000cl ●7179 .34400 231.000~ .Ills ●3690o 24.0000 ●8246 .3940
0 25.0000 .8780 ●4200o 26s0000 .9313 .4460
0 27.0000 .9846 .4730
0 30.0000 .9150 .5700
0 3s00000 1.0200 .7450
0 40.0000 1.0750 ●9200
o 45.0000 1.0850 1.0750
0 50.0000 l*i1400 1-2150
0 55’00000 .!3650 103450
0 60m OO!)0 .8750 1.4700
0 65e OOO0 .7650 1.5750
0 70.0000 *6500 1.6650
0 751.0000 ●5150 1.7350
0 80.0000 .3700 1-7800
0 85a000i) .2200 la8000
o 90.0000 .9700 1080000 95.0000 -.0700 1.7800
0 100.0000 -.a~oo 1.7500
0 Io:1.000tl -.3700 1.7000
0 llCI*OOOO -*51OO 1*6350o 11500000 --6250 1.5550
0 120.0000 -.7350 1.4650
19
Table 2. (cent)
~ 125-0000 -,8400 1.35000 130.0000 -09100 1-22500 135.0000 -.9450 1-08500 140.0000 -.9450 .9250
0 145.0000 -.9100 .7550
0 1s000000 -.8500 .57500 155.0000 -.7400 .42000 160*0000 -.6600 ●3200O 165-0000 --6750 .2300
0 17000000 -08500 ●1400o 175.0000 --6900 .0550
1 18000000 0.0000 ●0250700000.0 $JACA 0012 SECTION DATAt EPPLER 1403ELt C.s CDS DEC78
o 43.0000 0.0000 ●0067o 1.0000 .1100 .0068
0 2.0000 .2200 .00700 3.0000 .3300 ●0075
o 4.0000 .4400 .00830 5.0000 .5500 .00970 6s0000 ●6600 .0108
0 7.0000 .7700 .0118
0 8.0000 .8800 -01280 9.0000 ● 9598 .01440 10.0000 1.0343 .01590 1100000 1.0749 .01750 1200000 1.0390 .01950 13.0000 ● 8737 .02160 14.0000 ●6284 .0236
0 15.0000 .4907 .11700 16.0000 -4696 .21000 17.0000 ●5195 .23000 18.0000 ●5584 .2520
0 1900000 s6032 ●2740o 20.0000 ●6474 .2970
0 2100000 ●6949 .32000 22.0000 ●7446 .3440
0 23.0000 ● 7948 s369tlo 2400000 ●8462 .39400 25.0000 ●8984 -42000 26.0000 .9506 .44600 27-0000 100029 .4730
0 30.0000 .9150 .57000 35.0000 1.0200 .74500 40.0000 1.0750 .92000 45.0000 10085O 1.07500 50.0000 1.0400 1.21500 5500000 -9650 1034500 60-0000 .8750 1.47000 6500000 .7650 1.57500 70.0000 s6500 - 1*6650
20
Table 2. (cent)
o 75.0000 .5150 1.7350
0 /30.0000 .3700 1.7800
0 /35.0000 .2200 1.8000
0 9000000 .0700 108000
0 95.0000 -.0700 la7800
o 1[10.0000 -.2200 1.7500
0 10500000 -.3’700 1.70000 1:1 O*OOOO -.5100 1.6350
0 1:15.0000 -.6250 1.5550() l:~o.000o” -.7350 1-4650
0 1:25s0000 -.8400 1.3500
0 1:30.0000 -.9100 1s2250o 1:35.0000 -.9450 1-0850
0 1+0.0000 -.9450 -9250
0 1’$500000 -.9100 .7550
0 1!50-0000 -.8500 .5750
0 1!55.0000 -.7400 .4200
0 1150.0000 -s6600 ●3200
o 165.0000 -s6750 ●2300
o 1’70.0000 --8500 .1400
0 1“75.0000 -s6900 .0550
1 1/30.0000 000000 .0250
100000000 YACA 0012 SECTION DATA* EPPLER t400Ei_t C.s CDS DZC78
o 0.0000 0.0000 .0065
0 100000 .1100 sO066
o 2.0000 .2200 .0068
0 3.0000 .3300 .0071
0 4.0000 .4400 -0078
0 5.0000 .5500 .0091
0 6-0000 ●6600 ●O1O1
o 7.0000 .7700 *O11O
o 8-0000 ●8800 .0119
0 9.0000 .9661 .0134
0 :1000000 1.0512 .0147
0 .kl.0000 1*1097 .0162
0 :1200000 1.1212 ●0183
o :13*0000 1.0487 .0200
0 :1400000 ●8846 .022?
o :15.0000 ●7108 ●0245
o :15.0000 .6060 .1280
0 :17.0000 ●5906 -2310
0 18-0000 ●6030 s2520
o :19.0000 ●633ft .27+0
o ,20.0000 ●6716 .2970
0 !21.0000 ●7162 ●3200
o 22.0000 ● 7613 .3440
0 23s0000 .8097 .3690
0 24.0000 ● 8589 .3940
0 25.0000 .9093—.
●4200
.0 2600000 ●9618 .4460
21
Table 2. (cent)
o 27-0000 1.0144 .47300 30.0000 .9150 .57000 35.0000 100200 .74500 40.0000 1.0750 ●9200o 45.0000 1.0850 1.07500 50.0000 1.0400 1.21500 55.0000 .9650 1.34500 6000000 .8750 1.47000 65.0000 -7650 1.57500 70.0000 .6500 1.66500 7500000 .5150 1073300 80.0000 .3700 1.78000 85-0000 .2200 1.80300 90.0000 .0700 1-80000 9500000 -.0780 1-78000 100.0000 -.2200 1.75000 105.0000 -.3700 1.70000 110.0000 -.5100 lm6350o 115.0000 -e 6250 1055500 120.0000 -.7350 10465O0 125.0000 --8+00 1.35Lloo 130.0000 -.9100 1-22500 135* OCO0 -.9450 1-08500 140.0000 -.9450 .92500 145.0000 -.9100 .75500 150.0000 -.8500 .575’20 155.0000 -.7400 -42000 160.0000 -06600 ●3200O 165s0000 -.6750 .23000 170.0000 -.8500 *.1400o 175.0000 --6900 .05501 18000000 0.0000 ●02’50
2000000.0 NACA 0012 SECTION DATA? :PPLER MO)ELS C-s CD* DCC”78o 0.0000 ,0.0000 ●0064o 100000 ●11OO .00540 2.0000 .2200 .00s6o 3.0000 .3300 .00590 4.0000 .4400 900730 5.0000 .5500 .00!31o 600000 ●6600 .00’300 7.0000 .7700 .00970 800000 .8800 .01050 9.0000 .99000
.011310.OOOQ 1-0727 .0128
0 11.0000 1.1539 .01400 1200000 1.2072 .01550 13.0000 1-2169 .01720 14.0000 1.1614 .01910 1500000 1-0478 .0,2130 16s0000 .9221—— -023?-.
,
22
Table 2. (cent)
o 1700000 ● 7826 -13800 18s0000 ●7163 -25200 19.0000 .7091 .2740
0 20.0000 m 7269 ●2970
o 21.0000 .7595 ●3200
o 22.0000 ,7981 *3440
o 23-0000 *8423 s3690o 24.0000 .8892 .39400 25.0000 .9352 .4200
0 2s 00000 .9842 s4460
o 27.0000 1.0355 .4730
0 30.0000 .9150 .5700
0 35.0000 1.0200 .7450
0 40.0000 1.0750 ●9200
o 45.0000 lm0850 1.0’7500 5000000 1.0400 1.21500 55.0000 ● 3650 1.3*5Oo 60s0000 .8750 1.47000 65. ooao . “7650 1.57500 70.0000 .’5500 1.66500 75.0000 .5150 1.73300 800(10L10 .3-/00 1-78000 8500000 .2200 l.aoooo 90.0000 ●(1700 1080000 95.0000 -.0700 1-78000 100.0000 -.2200 1.7500
0 10500000 -.3700 1070000 110.0000 -*51OO lm6359o 115.0000 --6250 1.5550
0 120.0000 -.7350 1.46500 12500000 -.8400 1.35000 130.0000 -.9100 1.22500 135.0000 -.9450 1-08500 140.0000 -.3450 ●9250
o 145.0000 -.3100 .7550
0 150.0000 -.a500 .5750
0 155.0000 -.7400 ●4200
o 160.0000 -.6600 ●3200
O 165-0000 -.6750 ,23090 170.0000 -.a500 .1400
0 175.0000 -05900 .05501 180.0000 0.0000 .0250
500000090 NACA 0012 -SECTION !3ATAs :PPLER M03EL~ C.s CDS DEC78o 0.0000 0.0000 .0064
0 1.0000 .1100 .00540 2.0000 .2200 .00s6o 3.0000 .3300 .00680 4.0000 .4400 .00720 500000 .5500 .00760 5.0000 ● 6600 .0081
23
Table 2. (cent)
o 7.0000 .7700 ●0036o 8*00110 .8800 .00920 900000 .9900 .00980 10* OOOO 101000 .01060 1100000 la 1842 .0118 .0 12.0000 1.2673 .01300 13.0000 1s3242 .01930 14.0000 103423 .01590 15.0000 1.3093 .01770 1540000 102195 ●0198o 1700000 1.0365 .02290 1800000 .9054 ●1480o 19.0000 ●8412 .2740
0 20.0000 ●8233 .29700 2100000 ●8327 -32000 22.0000 .8563 .34400 2300000 ●8903 ,36900 24.0000 ●9295 .39400 2500000 ●9718 -4200
0 26-0000 1.0193 .44600 27.0000 1.0680 .47300 30.0000 .9150 .57000 35.0000 100200 .74500 40.0000 1.0750 -92000 45.0000 1.0850 1.07500 50.0000 1.0400 1.21500 55.0000 ● 9650 1.34500 60.0000 .8750 1.47000 65.0000 .7650 1.57500 70.0000 .6500 1.66500 75.0000 .5150 1073500 80.0000 .3700 1.78000 85.0000 .2200 1.80000 90.0000 .0700 1.80000 95.0000 -.0700 1078OO0 100.0000 -.2200 1.75000 105.0000 -.3700 1.70000 110.0000 -*51OO 1s6350o 115.0000 -=6250 1.55300 120.0000 -.7350 1.46500 12500000 -.8400 1.35000 130.0000 -09100 1=2250o 13500000 -.9450 1008500 140.0000 -.9450 ●9250o 145.0000 -.9100 .75500 150.0000 --8500 .5750,0 155.0000 -.7400 .420!3O 160.0000 -s6600 .32000 165s0000 -.6750 -23000 170.0000 -.9500 .1400
#
*
24
Table X (cent)
o 175.0000 -.6900 .05501 180s0000 0.0000 ●0250
10000000.0 NACA 0012 SECTION DATAY EPPLER MODEL* C.? CDS 0EC78o 0.0000 0.0000 .0054
0 1.0000 .1100 .006+
o 2.0000 .2200 .0066
0 3.0000 .3300 .00680 4.0000 .4400 .00710 5.0000 .5500 .00740 6.0000 .6600 .00780 7.0000 .7700 .0082
0 8.0000 .8800 .0086
0 9.0000 .9900 .00910 10.0000 1*1OOO .00970 11.0000 102100 .01040 12.0000 102906 ●0116o 13.0000 1-3687 ●O127o 14.0000 1*4171 .01410 15.0000 1*4214 .01570 16.0000 102941 -01820 1700000 1.1200 .0210
0 18s0000 .9795 ●0241o 19.0000 ● 8983 ●1610o 20.0000 .8668 .29700 21.0000 ,8665 ●3200
o 2200000 s 8859 .34400 23s0000 ● 9151 .3690
0 24.0000 -9492 .39400 25-0000 ● 9927 ●4200
O 2600000 100371 .4450
0 27-0000 1-0833 .4730
0 30.0000 ●9150 .5700
0 35,0000 1.0200 .7450
0 40.0000 100750 .9200
0 45.0000 1.0850 1.075fl
o 5000000 100400 1.21500 55.0000 .9650 1.3450
0 60.0000 .8750 1.47000 65.0000 .7650 1.5750
0 70.0000 .6500 1.66500 75.0000 .5150 1.7350
0 80.0000 .3700 1.78000 85.0000 .2200 1.80000 90.0000 .0700 1080000 9500000 -.0700 1-7800
0 100.0000 -.2200 1.75000 105.0000 -.3700 1.”7000
0 110.0000 -.5100 1-63500 115.0000 --6250 1.55500 120.0000 -.7350 10465O
25
Table 2. (cent)
o 125.0000 --8400 1.35000 130.0000 -.9100 1.22500 135.0000 -.9450 10085O0 140.0000 -.9450 .9250
0 145.0000 -.9100 .’7550
0 15000000 -.8500 .57500 155.0000 -.7400 .4200 :
0 160s0000 -.6600 .32000 16500000 --6750 ●2300o 170.0000 -08500 .14000 17500000 --6900 .05502 180.0000 0.0000 .0250
26
Table 3. Lift and Drag Coefficients for the NACA- 0015 Airfoil (104 s Re s 107
Re
10000.0 !JACA 001!5 SECTION OATA~ ZPPLER M03ELs C.t CDS 9EC 78
CY Cgcd
o 0.0000 0.0000 s0360o 1.0000 .0434 s0362o 2.0000 .0715 .03560 3.0000 -0725 .03730 4.0000 .a581 .03830 5.0000 ●0162 .03930 6-0000 -.0781 .04000 7.0000 -.1517 .0510
0 8.0000 -*1484 ●06400 9.0000 -.1194 .0770
0 ;10.0000 -.0791 .09100 :l.ls OOOO -.0348 *107Oo :12.0000 .0138 -12300 :1300000 .0649 .14000 :14.0000 ●1172 .15800 11500000 .1705 .17700 :16.0000 *2242 .19600 17sOOO0 .2780 .21’700 :LE3.0000 ●3319 ●.2380o 119-0000 ●3859 ●2600o 2000000 ● 4399 .28200 21.0000 .4939 .3050
0 22.0000 ●5479 ●3290(1 23.0000 ●6019 .35400 24.0000 ● 6559 .37900 2!5.0000 .7099 .40500 25.0000 .7639 ●4320o 27.0000 .8174 ●4603o :30.0000 .8550 .57000 35.0000 .9800 .74500 40.oo(lll 1.0350 ●9200o 45*oooa 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 .9550 1034300 60.0000 .8750 1.47000 ~~.000(j ●7600 1057500 1’0.0000 .6300 1-6650i 75.0000 ●5000 1.73500 83.0000 .3550 1.78000 85.0000 ●2300 1080000 90.0000 .0900 1.8000
0 5)5.0000” -.0500 1,78000 lCIO.0000 -.1850 1.75000 10500000 -03200 1.7000
0 11.0.0000 -.4500 l-635fJ
o 11,5.0000 -05750 1.55500 12!0.0000 -.6700 1.4650
27
Table 3. (cent)
@_ 12500000 -.7600 1.3500—
o 130.0000 -.8500 1*225!I
o 13500000 -.9300 1.08500 140.0000 -.9800 .92500 14500000 -.9000 .7550 .0 150.0000 -.7700 .57?50
o 155.0000 --6700 -4200
0 160=0000 -.6350 ●3200 b
o 165.0000 --6800 ●2300o 170.0000 -.8500 .1400
0 175.0000 -.6600 .0550
1 180-0000 0.0000 ●025020000.0 NACA 0015 SECTION DATAs EPPLER M03ELs CL? C2S DEC 78
0 ‘0.0000 0.0000 .0265
0 1.0000 s0891 .02670 2.0000 .1740 .02710 3.0000 .2452 .02790 4.0000 .3041 .02900 5.0000 ●.3359 .03030 5.0000 .3001 ●O41O
o 7.0000 .0570 .05100 8.0000 -.1104 .06400 9.0000 -.1050 .0770
0 10.0000 -,0728 ●O91Oo 11.0000 -.0300 .10700 12.0000 .0173 .12300 1300000 ●0678 .14000 14.0000 ●1193 .15800 1500000 .1721 .17700 1500000 ●2256 -19600 17.0000 ●2792 -2170
0 1800000 .3331 ●2380o 1900000 .3869 -26000 20.0000 .4409 .28200 21.0000 .4949 .3050
0 22.0000.
.5489 .3230
0 23-0000 ,6029 .35400 24.0000 .6569 .3730 *o 25s0000 .7109 .40500 26s0000 ●7643 -43200 27-0000 .8191 s4600o 30.0000 .9550 .5700
0 35.0000 .9800 .74500 40.0000 1.0350 .92000 45.0000 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 .9550 1.34500 60.0000 .8750 1.47000 65.0000 .7600 1.57500 70.0000 .6300 1.6650
28
Table :3. (cent)
o 75.0000 S5000 1.73500 80-0000 ●3650 1.78000 85s0000 ●2300 1080000 90.0000 .0900 1.80000 95.0000 -.0500 le7800o 100.0000 -.1850 1.75000 10500000 --3200 1070000 110.0000 -.4500 le6350o 115.0000 -.5750 1055500 120.0000 --6700 1-46500 125=0000 -=7600 1.35000 130.0000 -m8500 1.2250
0 135.0000 -09300 10085O0 140.0000 -.9800 .92500 145.0000 -.9000 .7550
0 150.0000 -.7700 .5750
0 15’500000 -e6700 .4200
0 160.0000 --6350 ●3200
O 16’500000 -.6800 ●2300o 17’3.0000 --8500 .1400
0 17’500000 -.6600 .0550
1 1810*0000 0.0000 .025040000.0 NACA 0015 SECTION DATAs EPPLER M03ELs C-s C2s DEc 78
0 0.0000 0.0000 .01960 ,100000 ● 1054 .01980 :2.0000 .2099 .0202
0 3.0000 .3078 .0209
0 400000 .4017 ●0219o :500000 .4871 -02320 600000 .’5551 -02490 ‘7.0000 .5730 ●0267
o [3.0000 ●4663 -0520
0 ‘3.0000 .0433 .0”770
0 10*OOOO -.0413 ●O91O
o l:L.0000 -.0144 .1070
0 12.0000 .0261 -12300 1.3*0000 .0741 .1400
—
o 14.0000 ●1244 .1580
0 1!5.0000 .1756 .1770
0 1$.0000 .2280 .19600 1“7.0000 .2815 ●2170o 11300000 .3351 -23800 1!1.0000 ● 3889 ●2600
o 2000000 ●4427 ●2820
o 2:100000 ●4966 .3050
0 22.0000 .5506 -3290
0 2;300000 .6045 .3540
0 2400000 e6585 .3790
0 25.0000 -7125 .4050
0 26.0000 ● 7666 .4320
29
Table 3. (cent)
o 27s0000 ●8222 -4600
0 30.0000 ●8550 .57000 35.0000 .9800 .74500 40.0000 1.0350 ●9200o 45.0000 1.0500 1.0750
0 50.0000 1.0200 1.2150:
0 55.0000 .9550 1034500 So.000o s8750 1.47000 65.0000
.●7600 1.5750
0 70.0000 .6300 10665O
0 75.0000 ●5000 1.7350 -
0 80.0000 .3550 lm7800o 85-0000 ●2300 1.8000
0 90.0000 .0900 1-80000 95.0000 -.0500 1-7800
0 100.0000 --1850 1.7500
0 105.0000 -.3200 1.’70000 110.0000 -.4500 10635O0 115.0000 -.5750 1.5550
0 120.0000 -06700 1.46500 125.0000 -.7600 1.35000 130.0000 -.9500 1s2250
o 135.0000 -.9300 1.0850
0 140.0000 --3800 ●9250o 145.0000 -.9000 .7550
0 150.0000 -.7700 .575?o 155.0000 -.6700 ●4200
o 160.0000 -.6350 -3200
0 16500000 -.6800 ●2300o 170.0000 -=8500 .14000 175.0000 -.6600 .05’50
1 180eOOOG 0.0000 .0250
8000000 NACA 0015 SECTION DATA? EPPLER M03ELs C-s CD? DEC 780 0.0000 0.0000 .0147
0 100000 .11?)0 .01480. 2.0000 .2200 .0151
.
0 3.0000 .3300 ●0156o 4.0000 ●4186 .01680 5.0000 .5180 .0181
‘
o 5.0000 .5043 .0197
0 7.0000 .6760 .0214
0 800000 07189 s0234o 9.0000 ,6969 s0255o 10.0000 ●5122 -0277
0 11.0000 ● 1642 s0760o 12.0000 .0749 ●1230o 13.0000 .0967 .1*OJo 14.0000 .1382 .158!3o 15.0000 ●1861 .17700 16-0000 ●2364 .1960
30
Table 3. (cent)
o 17.0000 ●2873.—
●2.1700 1!3.0000 ●3393 =238!I0 19.0000 ●3927 ●26000 20.0000 .4463 .28200 211.0000 .5001 .3050il z;~.000o
● 5539 ,32900 2.300000 s6078 .35400 24.0000 06617 .37900 2!5-0000 ●7156 .40500 2600000 .7700 .4320(1 27.0000 ●8277 s4600o 30.0000 ●8550 .57000 35. t1000 .9800 .74500 4(1.0000 1.0350 .92000 4?5.’0000 100500 1007500 50.0000 1*0200 10215O0 55.0000 .9550 1.34500 60s0000 ●8750 1.47000 65.0000 .7600 1.57500 70.0000 .6300 1.6650c1 75 QOO00 ●5000 1.73500 8[)00000 .3650 la7800o 85.0000 ●2300 1.80000 9(1.0000 .0900 1-80000 95.0000 -.0500 1-78000 100.OOOO --1850 1.75000 105.0000 --3200 1.70000 11000000 -.4500 1s6350o 115.0000 -05750 1055500 120.0000 -.6700 1.46500 125.0000 -.7600 1.35000 13(1.0000 -.8500 1-22500 13:1.0000 -.3300 1-08560 140.0000 -.3800 .92500 145.0000 -.9000 .75500 15CI.0000 -.7700 .57500 155.0000 -.5700 .42000 16(1.0000 -.6350 .32000 155.0000 -.6800 .23000 170*OOC0 -.3500 .14000 175.0000 -.6600 .05501 18CI.0000 0.0000 .0250
lf50000.tl VACA 0015 SECTION f3ATAv EPPLER M03E,L? C.? CDS DEC 780 0.0000 0.0000 .01130 1,00000 ●11OO .01170 :!00000 .2200 .01200 300000 .3300 •ol~4
o 4.000J .4400 .01320 590090 .5500 -01420 5’.0000 .5299 .0150
31
Table 3. (cent)
o 7.0000 .7150 :01760 8-0000 ●7851 .01930 9.0000 ●8311 .02120 10.0000 ●8322 ●0233o 11.0000 ●7623 ●0256o 12.0000 .5936 .02810 1300000 ● 3548 ●0302
:
0 14.0000 ●2371 .1040 ,
0 15.0000 ●2376 .17700 ‘1s.0000 ●2665 .19700 1700000 ●3098 *2170O 18.0000 ●3567 ●2380o 1900000 .4066 .26000 20.0000 .4575 .2820
0 ‘21.0000 .5087 .30500 22.0000 ●5611 .32900 23s0000 ●6148 .35400 24-0000 ● 6685 .37900 25-0000 ● 1224 .40500 26-0000 e 7771 ●4320o 27s0000 ●8382 ●4600o 30.0000 .8550 .57000 35.0000 .9800 .7450
0 4000000 1.0350 .92000 45.0000 1.0500 1.07500 50.0000 190200 1.21500 55.0000 ●9550 1.34500 60.0000 .8750 1.47000 65-0000 .7600 1.57500 70.0000 s6300 10665O0 75.0000 .5000 1.73500 80.0000 s3650 1.78000 85.0000 .2300 1.80000 90.0000 .0900 1-80000 95.0000 -.0500 1.78000 100.0000 -.1850 1.7500
.
0 105.0000 -s3200 1.70000 11000000 -.4500 1,63500 115.0000 -.5750
*1.5550
0 120.0000 -.6700 1.46500 125.0000 -.7600 1.35090 13000000 --8500 1.22500 135.0000 -.9300 1=0850
— —
o 14000000 -.9800 ●9250o 14500000 -.9000 .75500 15000000 -.7700 .57500 155.0000 --6700 .42000 160.0000 -.6350 .32000 155.0000 -.6800 ●2300o 1“70.0000 -.8500 .1400
32
Table :3. (cent)
o 175.0000 -.6!500 .05501 180.0000 0.0000 .0250
360000.0 NACA 0015 SECTION DATAY EPPLER FIO)ELS C.Q CJ~ 3EC 780 0.0000 0.0000 .00910 100000 .1100 .00920 2.0000 .2200 .00940 3.0000 .3300 .00980 4.0000 .+400 .01050 5.0000 .5500 .01140 6.0000 .6600 .01260 7.0000 97390 .01430 8.0000 .8240 .01570 9.0000 .8946 .01730 10.0000 .9440 .01310 11.0000 ●9572 ●0211o 12.0000 .9285 -02330 13.0000 .8562 -02570 14.0000 .7483 ●0283o 1500000 .6350 -03120 16.0000 .5384 .12400 17.0000 ●4851 .21700 19.0000 .4782 .23800 1’9.0000 m4908 .26000 2’0.0000 .5247 .28200 21.0000 ●5616 .30500 2<2.0000 .6045 .32900 23.0000 .6528 .35400 2’4.0000 .7015 .37900 2!500000 .7511 .40500 26.0000 .8055 .43200 27.0000 .8788 .46000 3i0.0000 .8550 .57000 3!5.0000 .9800 .74500 411.0000 1.0350 ●9200o 4!5.0000 1.0500 1.07500 50.0000 1.0200 1.21500 5!5.0000 .9550 1.34500 611.0000 ● 8750 1.4’7000 6!5.0000 .’7600 1.57500 70.0000 .5300 1966500 7!5.0000 .5000 1.73500 8[1.0000 .3650 1078OO0 8!5.0000 .2300 1.80000 90.0000 .0900 1080000 9!500000 -.0500 1.78000 10000000 ‘.1850 1.75000 10!5.0000 -.3200 1.70000 110.0000 -.+500 1.63500 115.0000 -.5750 1.55500 12000000 -*670il 10465O
33
Table 3. (cent)
O 125.0000 -.7600 1035000 130.0000 -.8500 1.22500 135.0000 -.9300 1.08500 14000000 -.9800 .92500 145.0000 -.9000 .75500 150.0000 -.7700 .57500 155.0000 -.6700 .4200
0 160.0000 -.6350 .3200 .
0 165.0000 -.6800 .23000 170.0000 -.8500 .14000 175.0000 -.6600 .0550
1 180.0000 0.0000 .0250700000.0 NACA 0015 SECTION DATAs EPPLE3 MODELS CLt CDS DEC 78
0 0.0000 0.0000 .00770 l*OOO!I .1100 .00780 2.0000 .2200 .00800 3.0000 .3300 .00830 4.0000 .4400 .008!3o 5.0000 .5500 .00980 6.0000 .6600 .0108
0 7.0000 .7483 .01220 8.0000 .a442 .0135
0 900000 .9260 .0149
0 10.0000 .9937 .01640 11.0000 100363 .01820 12.0000 100508 .0200 ,0 1300000 1.0302 .02210 1+00000 .9801 ●0244o 1500000 .9119 .02%39o 16.ooclo .8401 .02970 17.0000 ● 7799 .13400 18.0000 .7305 .23800 13*OOOU .7041 .2600
0 20.0090 .6990 .2820
0 21.0008 .7097 .3050
0 22.0000 .7298 .3290.
0 23.0000 .7593 .35400 24.0000 .7361 .3790
0 25.0000 ●8353,
.40500 2590000 .8838 .4320
0 27.0000 ●9473 .+600o 30*OOOC .!3550 .57000 3500000 .9800 .7450
0 40.0000 1.0350 .9200
0 45.0000 1.0500 1.07500 50.0000 1.0200 1.2150
0 55.0000 .9550 1.34500 60.0000 .875~ 1.470G
-ii 65.0000 .7600 1.5750
0 70.0000 .6300 106650
34
o 75.0000 .5000 1.73500 804,0000 .3%50 1.78000 85,0000 .2300 le8000
o 90.0000 .0900 1.80000 95!.0000 -.0500 1.78000 100(,0000 -.1850 1.75000 105,0000 -.3200 1.7000
0 1104BOOOO -.4500 1.63500 115,0000 -.5750 1.5550
0 120!,0000 -.6700 1.46500 125(,0000 -.7600 1.3500
0 130.0000 -08500 1.22500 135!,0000 -.9300 1.0850
0 140? OOO0 -.9800 .92500 145(00000 -09000 .7550
0 150!moooo -.7700 .5750
0 155!00000 -.6700 .4200
0 160,.0000 -.6350 .32000 165mOOO0 -.6800 .23000 170*0000 -.8500 .1400
0 1751.0000 -.6600 .0550
1 180+.0000 0.0000 .02501000(IOO*O VACA 0015 SECTION DATAs :PPLER M03ELs C.z CDS JEC 78
0 04,0000 000000 .0074
0 1<,0000 .lldo .0075
0 24,0000 *2200 .00760 34,0000 .3300 .0079
0 4,,0000 .4400 .00830 5{,0000 .5500 .oo~l
o 6,,0000 .6600 .0101
0 7,,0000 .7700 .01110 8(,0000 .8504 .01260 94,0000 .9387 .01380 10,)0009 1.0141 .01520 114)0000 1.0685 .01680 12(.0000 1.0971 .01960 13!,0000 1.0957 .020<;
3 144)0000 1.0656 ●0225
o 154)0000 1.0145 .02430 164,0000 ● 3567 .0275
0 17{,0000 .8996 .0303—
o 18<)0000 =8566 .14500 194)0000 .8226 .2600
0 20<00000 .3089 .28200 2100000 s8063 .30500 22(00000 .8189 .3290
0 23{)0000 .8408 .3540
0 24400000 .8668 .3790
0 251,00d0 .9023 .4050
0 254)0000 .9406 .4320
35
Table 3. (cent)
— . .0 27.0000 .9912 .46000 30.0000 .8550 .57000 35.0000 .9800 .74500 40.0000 1.0350 ●9200o 45.0000 1.0500 1.07500 5000000 100200 1.21500 55.0000 .9550 1.34500 6000000 .8750 1.47000 65.0000 .7600 1.5750
.
0 70.0000 .6300 10665O0 75.0000 .5000 1.73500 80.0000 .3650 1.78000 85.0000 .2300 1080000 9000000 ●0900 1.80000 95.0000 -.0500 1.78000 100.0000 -.1850 1.75000 105* OOOO -.3200 1.70000 11000000 “-.4500 1.63500 115.0000 -.5750 1.55500 120.0000 -.6700 1.46500 125.0000 -.7600 1.35000 130.0000 -08500 1.22500 135.0000 -.9300 1.08500 140.0000 -.9800 .92500 145.0000 -.9000 .75500 150.0000 -.”7700 .57500 155.0000 -.6700 ●4200O 160s0000 -e6350 .32000 16500000 -.6800 .23000 170.0000 ‘.8500 .14000 175.0000 -.6600 ●05501 180.0000 0.0000 .0250
2000000.0 NACA 0015 SECTION !3ATAz SPPLER MODEL? C.s CDt 12EC 780 0.0000 0.0000 .00700 100000 .1100 .00710 2.0000 .2200 .0072 .
0 3.0000 .3300 .00750 4.0000 .4400 .00780 5.0000 .5500 .0083
●
o 500000 .6600 .00900 7.0000 .7700 .00980, 8.0000 .8800 .01080 9.0000 .9574 .01210 10.0000 1.0433 .01330 1100000 1.1138 ●0146o 12.0000 101667 .01610 1300000 101948 .01770 19.0000 1*1962 .01950 1500000 1*1744 .02150 16.0000 1.1356 .0237
36
Table 3. (cent)
o 1,7.0000 100921 .02610 1.8.0000 1* O51O .0288Q 19.0000 1.0173 .15500 :!000000 .9954 .28200 :!100000 .9837 .30500 2!2.0000 99827 .32900 2!3.0000 ●991O .35400 2!4. 0000 1.0078 .37900 2!500000 1.0317 .40500 2!6.0000 1.0591 ,43200 2!7.0000 1.0810 .46000 21000000 .8550 .57000 35.0000 .9800 .74500 40.0000 100350 .92000 45.0000 1.0500 1.07500 50.0000 100200 1.21500 55.0000 .9550 1.34500 60.0000 .8750 1.47000 65.0000 .7600 1.57500 70.0000 .6300 10665O0 75.0000 .5000 1.73500 80.0000 ● 3650 1.78000 85.0000 .2300 1.80000 90.0000 .0900 1.80000 95.0000 -.0500 1.78000 100.0000 -.1850 1.75000 105.0000 -.3200 1.70000 110.0000 -.4500 1.63500 115.0000 -.5750 1.55500 120.0000 -.6700 1.46500 125.0000 -s7600 1035000 130.0000 -.8500 1.22500 135.0000 -.3300 10085O0 140.0000 -.9800 .92!5flo 145.0000 -.9000 .75500 150.0000 -.7700 .57500 155.0000 -.6700 .42000 160.0000 -.6350 .32000 165.0000 -.6800 .23000 170.0000 -08500 .14000 175.0000 -*15600 .05501 18000000 0.0000 ●0250
5000000.0 tIJA3A 0015 SECTION DATA> :PPLER M03ELs CLF CD* 2EC ?8o 0.0000 0.0000 .00580 100000 .1100 900690 200000 .2200 .00700 300000 .3300 .00730 9.0000 .4400 .00750 ‘500000 .5500 .00800 5.0000 .6!500 -0084
37
Table 3. (cent)
o 7.0000 .7700 .00890 8.0000 .8800 .0095
0 900000 .9900 .01020 10* OOOO 100685 .01130 11.0000 1.1553 .0124
0 12.0000 1.2290 .01360 1300000 102847 .01490 1300000 102847 .0149 #
o 14.0000 1.3187 .01640 15.0000 1.3298 .01800 16.0000 1s3186 .01980 ‘17.0000 1.2917 .02180 18.0000 102576 .02400 19.0000 1.2242 .02550 20.0000 1*1965 .1660
0 21.0000 1.1771 ●3050o 22.0000 1.1647 .3290
0 23.0000 1.1611 .35400 2400000 1.1563 .37900 25.0000 1.1322 ●4050o 26.0000 le1268 .4320
0 27s0000 1.1397 .46000 30.0000 .8550 .5700
0 35.0000 .3800 .7450
0 40.0000 1.0350 .92000 45.0000 1.0500 1007500 50.0000 1.0200 1.21500 55*ooclo .9550 1034500 60.0000 .8750 1.4700
0 65.0000 .7600 1057500 70.0000 .6300 1.66500 7500000 .5000 1.73500 80.0000 .3650 1.78000 8500000 .2300 1.80000 90.0000 .0900 1.80000 9590000 -.0500 1.78000 100.0000 -.1850 1.75000 105.0000 -s3200 1.70000 110.0000
.
-.4500 1.63500 115.0000 -95750 1.55500 120.0000 -.6700 10465O0 125s0000 -.7600 1.35000 130.0000 -.8500 1.225(Io 13500000 -.9300 1.08500 140.0000 -.9800 ● 92500 145.0000 -09000 .75500 150.0000 -.7700 .57500 155.0000 -.6700 .42000 160.0000 -.6350 .32000 165.0000 -.6800 .2300
38
Table 3. (cent)
o 170.0000 -03500 ●1400o 175.0000 -.6600 .05501 180.0000 0.0000 .0250
~ooooo. o NACA 0015 SECTION OATA~ EPPLEil M03ELs CL? CO* DEC 780 000000 000000 .00680 100000 ●11OO .00680 2.0000 .2200 .00690 3.0000 .3300 .00710 4.0000 .4400 ●0074o 5.0000 ●5500 .00770 6.0000 .6600 .00810 7.0000 .7700 .0086
0 8.0000 .8300 .00900 9.0000 .9900 .00960 10.0000 101000 ●O1O3
o 11.0000 1*1749 .01140 12.0000 1*2591 .0123
~ 13.0000 1.3300 .01340 14.0000 1.3825 90147
15.00000 1.4136 .0161
0 16.0000 1.4233 .017617.00000 1.4136 .0194
0 18.0000 1.3897 .02130 19.0000 1.3608 .0234
0 20.0000 1.3325 .0257~ 21.0000 1.3077 .17700 22.0000 1.2767 .3290
23.00000 1*1981 .35400 24.0000 1.1538 .37900 25,0000 1.1380 .40500 25.0000 1*1374 .43200 27.0000 1.1519 .46000 30.0000 .8550 .57000 35.0000 .9800 .74500 40.0000 1.0350 .92000 45.0000 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 .3550 1.34500 50.0000 .8750 1.4700
0 65.0000 .7600 1.57500 70.0000 .6300 1.6650
0 75.0090 95000 1.73500 80.0000 .3550 1.7800
‘65.0000o .2300 1.80000 90.0000 .0900 1080000 95.0000 -.0300 1.78000 loo.000a -.lr350 1.75000 105.0000 -.3200 1.70000 110.0003 -.4500 1.6350
0 115.0000 -.5750 1.5550
39
Table 3. (cent)
o 120.0000 -.6700 1.4650
0 125.0000 -07600 1035000 130.0000 -.8500 1.22500 135.0000 -.9300 1.08500 140.0000 -.9800 .9250
0 14500000 -.9000 .75500 150.0000 -* 7700 .57500 155.0000 -.6700 .4200
.0 160.0000 -.6350 .3200
.0 165.0000 -.6800 .23000 170.0000 -.8500 .1400
0 175.0000 -.6600 .05502 180.0000 0.0000 .0250
.
.
.
.
40
Table 4. Lift and Drag Coefficients for the NACA- 0018 Airfoil (104 s Re s 5 x 106)—.
Re
~ 10000.0 NACA 0018 SECTION DATAs EPPLER M03ELs CLS CD? JAN 79
CY CRcd
o a1.000o 000000 .03.850 100000 -.0045 .03870 2!00000 -.0154 .03910 2)00000 -.0233 .03990 4’00000 ‘.0368 ●0410o 5.0000 -.0577 .04250 6100000 -.0839 .04430 1.0000 -.1182 .04630 8.0000 -01501 .04890 5).0000” -.1584 .05250 la.000o -.1423 .05740 11.0000 -.1125 .08000 12.0000 -.0767 .12300 14.0000 .0085 .15800 16.0000 .1051 s1960o 181.0000 .2070 .23800 20.0000 ●3111 .28200 22.0000 ●4172 .32900 25100000 ●5775 .40500 30.0000 .8550 .57000 35.0000 .9800 .74500 40.0000 1.0350 ●9200o 45.0000 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 ●9550 1.34500 60.0000 .8750 1047000 65.0000 .7600 1.5750
0 7000000 .6300 1.66500 75.0000 .5000 1.73500 80.0000 .3650 1.78000 85.0000 .2300 1.8000
0 9000000 .0300 1.80000 95.0000 -.0500 1.78000 100.0000 -.1850 1.75000 105* OOOO -.3200 1.70000 110.0000 -.4500 1.63500 115.0000 -.5750 1.55500 120.0000 -.6700 1.46500 125.0000 -.7600 1.3500
0 130.0000 -.8500 1.22500 135.0000 -.9300 1.08500 140.0000 -.9800 .92500 145.0000 -.9000 .75500 150.0000 ‘.7700 .57500 155.0000 -.6700 .4200
41
Table 4. (cent)
O 160.0000 -.6350 ●3200O 165-0000 -.6800 .23000 17000000 -.8500 .14000 175.0000 -.6600 .0550
1 180.0000 0.0000 .025020000.0 NACA 0018 SECTION DATA* EPPLER fI103ELs CLt CDS JAN 79 .
0 0.0000 0.0000 .02860 1.0000 .0607 .02880 2.0000 .1135 .0292
0 3.0000 .1550 .02990 4.0000 .1788 .03100 5.0000 .1788 .03230 6.0000 .1582 .03390 7.0000 .1161 .03580 8.0000 .0214 .03760 9.0000 -.0682 .03950 10.0000 -.1003 .06300 1200000 -.0602 .12300 14.0000 .0172 .15800 16.0000 .1114 .19600 18.0000 .2120 .2380
0 2000000 .3151 .28200 22.0000 .4198 .3290
0 2500000 .5798 .4050
0 30.0000 .8550 .5700
0 35.0000 .9800 .7450
0 40.0000 100350 .92000 45.0000 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 .9550 1034500 60s0000 .8750 1.4700
0 65.0000 .7600 1.57500 70.0000 .6300 1.6650
0 75*0000 .5000 1073500 80.0000 .3650 1.78000 85.0000 .2300 1.80000 90.0000 .0900 1.8000 ,
0 95.0000 ~ -.0500 1.78000 100.0000 -.1850 1075000 105.0000 -.3200 1.7000
t
o 110.0000 -.4500 1.63500 11’5.0000 -.5750 1.55500 120.0000 -.6700 1.465Co 125.0000 -.7600 1.35000 130.0000 -.8500 1.22500 13500000 -.9300 1.08500 140.0000 -.’3800 .92500 145.0000 -.9000 .75500 150.0000 -.7700 .5750
0 155.0000 -.6700 .4200
42
Table 4. (cent)
O 1.60-0000 -.6350 ●3200
o 1.65.0000 --6800 ●2300
o 1.70.0000 -08500 91400
0 1.75.0000 -.6600 .0550
1 1.8000000 0.0000 .0250
4000000 NACA 0018 SECTION DATAs EPPLER M02ELs C*S C2a JAN 79
0 000000 0.0000 -02140 1.0000 ● 0936 .0215
0 2.0000 .1833 .0219
0 3.0000 ●2688 ,0225
0 4.0000 .3495 .02350 5.0000 .4117 ●0247
o 500000 .4573 .0263
0 7.0000 .4758 .0282
0 ~.000o .4428 .0303
0 9.0000 ●3544 .0327
0 10.0000 .~lo8 .0620
0 12.0000 .0139 .1230
0 1400000 .0489 .1580
0 15.0000 .1287 .1950
0 18.0000 ● 2228 .2380
0 20.0000 .3236 .28200 22.0000 .4265 .32900 25-0000 .5840 .4050
0 30.0000 .8550 .57000 35.0000 s9800 .7450
0 40.0000 1.0350 .9200
0 45.0000 1.0500 1.07500 50.0000 100200 10215O0 55.0000 .9550 1.3450
0 60.0000 .8750 1.4700
0 65s0000 ● 7600 1.5750
0 7000000 .6300 1.6650
0 7500000 .5000 1*7350
o 8000000 ● 3650 1078OO
0 85-0000 ●2300 1080000 90.0000 .0900 1.8000
0 9500000 -.0500 le7800
o 1,00.0000 -.1850 1.7500
0 1105.0000 -s3200 1070000 I1O*OOOO -.ft?50?J 1.6350
0 311500000 -.5750 1.55500 120.0000 -s6700 144650
0 125*0000 -.7600 103500
0 1.30.0000 --8500 10225O
0 113500000 -09300 1-08500 1!4000000 -.9800 .9250
0 1145.0000 -.9000 .7550
0 1.50.0000 -.7700 .5750
0 ]L55.0000 -.6700 .4200
43
Table 4. (cent)
O 16000000 ”-”‘- -*6350 ●3200O 165.0000 -.6800 ●2300o 170.0000 -.8500 .14000 175.0000 -.6600 .05501 180-0000 0.0000 ●0250
80000-0 NACA 0018 SECTION OATA? EPPLER tlO)ELt C-s CD? JAN 790 0.0000 0.0000
*
s01620. 1.0000 ● 0889 ●0163o 2.0000 ●1935 ●0167o
b
3.0000 ●2924 s0172o 4.0000 .3880 901810 5.0000 .4753 -01920 600000 .561’5 .02060 7.0000 ●6224 .02230 8=0000 ● 6589 =0242o 9.0000 .6606 ●0264o 10.0000 ● 6248 .02880 11.0000 .5531 .03150 12.0000 ,4408 ●0800o 14.0000 ● 2256 .15800 16.0000 .2027 .19600 18.0000 s2603 ●2380o 20.0000 ●3472 .28200 22.0000 .4430 .32900 25.0000 ● 5963 .40500 30.0000 .8550 .57000 35.0000 ●9800 .74500 40.0000 1.0350 .92000 45.0000 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 * 3550 1.34500 60.0000 ●8750 1.47000 65s0000 ●7600 1.57500 70.0000 .5300 1.66500 75.0000 .5000 1.73500 8000000 .3650 1.78000 85.0000 .2300
,1.8000
0 90.0000 .0300 1-80000 95.0000 -.0500 1.78000 100.0000 -.1850 1.7500
.
0 105.0000 ‘.3200 1.70000 11O*OOOO -.4500 1-63500 11500000 -.5750 1.55500 120.0000 --6700 1.46500 12500000 -.7600 1.35000 13000000 -.8500 1.22500 13500000 ‘.9300 1908500 140.0000 -.3800 ●9250o 145.0000 -.9000 .75500 150.0000 -.7700 .5750
44
Table 41.(cent)
O 155.0000 -s6700 ●4200
O 16(1.0000 --6350 ●3200O 165.0000 -.6800 ●2300o 17000000 -.8500 .14000 175.0000 --6600 .05501 18(1s0000 0.0000 .0250
16(100000 NACA 0018 SECTION DATAs iPPLER MODELS C.S Ci)3 JAN 790 000000 000000 .01280 1..0000 .1100 ●0129o 200000 .2200 .01310 3.0000 .3088 .0137
0 4}.0000 ●4114 .0144
0 500000 .5068
0
●0153
6.0000 .5960 .01660 7’.0000 ● 6724 -01810 800000 .7373 .01980 !100000 ●7781 .02170 lC).0000 ● 7949 .02380 11.0000 *7852 .0262
0 1:!00000 ●7488 -02880 13.0000 ●6923 .07700 14}.0000 ●6237 .15800 151.0000 ●4896 ●1960o 18.0000 .+202 -23800 20.0000 ●4382 -28200 2:!00000 .5026 .32900 25.0000 ● 6321 .40500 30.0000 ●8550 .57000 35.0000 .9800 .74500 4t11.000o 100350 .92000 45.0000 100500 1.07500 50.0000 1.0200 1.21500 55.0000 .9550 1.34500 601eOOO0 .8750 1.4700
0 65.0000 .7600 1.57500 70.0000 .6300 10665O
.0 75.0000 .5000 1.73500 801sOOO0 ● 3650 1-7800
0 85.0000 .2300 1-80000 9CI*OOO0 .0900 1080000 95.0000 -.0500 1078OO0 10(I.OOOO -.1850 1.7500
0 10500000 -.3200 1.70000 11OI.OOOO -.4500 1.63500 1151.0000 -.5750 1.55500 120.0000 -.5700 1-4650
0 12500000 -.7600 1935000 130.0000 --8500 1.2250
0 13500000 -.9300 ‘1oO85Oo 140.0000 -.9800 .9250-—.-
45
Table 4. (cent)
-o 14500000 -.9000 ●’7550————.
o 150.0000 -.7700 .5750
0 155.0000 --6700 s4200
O 160s0000 -.6350 .32000 165-0000 -.6800 ●2300o 170.0000 -s8!500 .1400
0 175.0000 -.6600 .0550 “
1 180.0000 0.0000 -0250360000.0 NACA 0018 SECTION DATA~ EPPLER t40Z)ELs C-? CD* JAN 79
0 0.0000 0.0000 ●O1O1*
o 1.0000 ●11OO “ .0102
0 2.0000 .2200 ●O1O4o 3.0000 .3300 .01070 4.0000 .4400 .01120 5.0000 .5240 .0121
0 6-0000 ● 6228 ●0132o 7.0000 .7100 .01450 8.0000 -7879 .01590 9.0000 ●8526 ●0176o 1000000 .8983 .01940 11.0000 .9249 .02130 12.0000 .9279 -02350 13.0000 .9104 ●0259
o 14.0000 .8/303 .09400 16.0000 .8007 s1960O 18.0000 .7319 .23800 20.0000 869’37 s2820
o 2200000 .7050 -32900 25.0000 .7724 .40500 30.0000 .8550 .5700
0 35.0000 ●9800 .7450
0 40.0000 1.0350 ●9200o 45.0000 1.0500 1.0750
0 50.0000 1.0200 1.2150
0 55.0000 .9550 1.3450
0 60.0000 .8750 1.47000 65.0000 .7600 1.5750
.0
,
70.0009 .5300 1.66500 75.0000 .5000 1.7350
0 80-0000 .3650 1-7800 ,
0 85-0000 .2300 1.80000 9000000 .0900 1080000 95.0000 -.0500 1.78000 100.0000 -.1850 1.75000 105.0000 -.3200 1.70000 110.0000 -.4500 1.63500 115.0000 -.5750 1.55500 120.0000 -.6700 10465Oc1 125.0000 -.7600 1.35000 130.0000 -.8500 10225O
46
Table 4. (cent)
0 13500000 -.9300 10085O0 140.0000 -.3800 .9250
0 1451.0000 -.9000 .75500 150.0000 -.7700 .5759
0 155’00000 -e6700 ●4200
O 16000000 -.6350 .3200
0 1651.0000 -.6800 .23?30o 170.0000 -,8500 .14000 17500000 -.6600 .05501 18al*oooo 0.0000 .0250
7oalooo00 NACA 0018 SECTION DATA, EPPLER f109ELs C.? CDS JAN 790 0.0000 0.0000 .0085
0 100000 .1100 .00870 2!*OOO0 .2200 .0088
0 3.0000 .3300 .00910 4.0000 .4400 .00960 5.0000 .5500 .01020 6190CJO0 .6328 .0112
0 7’.0000 .7291 .01230 8.0000 .8156 .0136
0 900000 .8904 .01500 la.000o .9541 .0166
0 11.0000 .9973 .0183
0 12.0000 1.0245 .02020 13.0000 1.0289 .02230 14.0000 1.0175 .02450 15.0000 .9938 .10200 15.0000 .9648 .19600 la.000o .9150 .23800 20.0000 .8877 .28200 22!.0000 ● 8867 .32900 25.0000 .3326 .4050
0 3a1.000o .8550 .5700
0 351.0000 .9800 .74500 40.0002 1.0350 .92000 45.0000 1.0500 1007500 501.0000 100200 1.2150a 551.0000 .3550 1034500 60.0000 .8750 1.47000 65.0000 .7600 1.57500 7000000 .5300 1.66500 75.0000 ●5000 1.73500 8a’Oooou .3650 1.78000 85.0000 ●2300 1080000 90.0000 .9900 1.8000
0 95.0000 -.0500 1.78000 102.0000 -.1850 1.75,000 10500000 -.3200 1.70000 11O.OOOO -.4500 1.63500 115.0000 -.5750 1.5550
47
Table 4. (cOnt)
“O 12000000 ‘“ -.6700 1.4650 ““——
0 12500000 -.7600 1.35000 130.0000 --8500 1.2250
0 135.0000 -.9300 1.08500 140.0000 -.9800 .9250
0 14500000 -09000 .7550
0 15000000 -.7700 .5750,
0 155.0000 -.6700 .42000 160s0000 -.6350 .32000 16500000 -.6800 c2300
)
o 170.0000 -09500 .14000 175.0000 -06600 .05501 18000000 000000 .0250
100000000 NACA 0018 SECTION DATA> EPPLER M03ELs C.s CD* JAN 790 0.0000 0.0000 900820 1.0000 .1100 ●0082o 2.0000 02200 .00830 3.0000 .3300 .00860 4.0000 .4400 ,00890 5.0000 .5500 .00950 6.0000 .6600 .01020 7.0000 ● 7362 .01150 8.0000 .8256 .01260 9.0000 .9067 .01390 1000000 ●9751
o.0154
11.0000 100284 .01700 1200000 100664 s0187o 13.0000 100304 s0206o 14.0000 1.0793 .02270 15.0000 100624 .02510 1600000 1-0402 ●1080o 1800000 .9959 -23800 20.0000 ●9707 .28200 22.0000 ● 9696 .32900 25s0000 1.0107 .40500 30.0000 .8550 .57000 35.0000 .9800 .7450 ●
o 40.0000 1.0350 .92000 4500000 1.0s00 1.07500 50.0000 1.0200 10215O
,
0 55.0000 .9550 1.34500 60.0000 .8750 1.47000 65.0000 .7600 1.57500 \ 70.0000 .6300 1.66500 75.0000 .5000 1.73500 80.0000 ● 3650 le780(lo 85.0000 .2300 1-80000 90.0000 .0900 1.80000 95.0000 -.0500 1.78000 100.0000 ‘-.1850 1.7500
48
Table 4. (cent)
-——. —-0 lo5.0000- -.3200 1.70000 110.0000 -.4500 10635O0 115.0000 -.5750 1.55500 120.0000 -s6700 1.46500 125.0000 -.7600 1.35000 13000000 -08500 1.22500 135.0000 -.9300 1.0850
0 140.0000 -.9800 .92500 145.0000 -.9000 .75500 15000000 -.7700 .57500 155.0000 -.6700 -42000 160.0000 -.6350 .32000 165.0000 -.6800 .2300
0 170.0000 -.8500 .14000 175.0000 -.6600 .0550
1 180.0000 0.0000 .02502000000.0 NACA 0018 SECTION DATA? EPPLER M03ELs CL~ Cot JAN 79
0 000000 000000 .00770 1.0000 ●11OO .00770 200000 .2200 .00780 3.0000 .3300 .00!30
o 4.0000 .4400 .00840 5.0000 .5500 .00870 600000 .6600 .00930 7.0000 .7449 .01010 8.0000 .8439 ●0111o 900000 .9314 .01220 10.0000 1.0111 .01340 11.0000 1.0772 ●0148o 12.0000 1.1296 .01630 13.000fl 1.1662 .01790 14.0000 1.1813 .01970 15.0000 1.1813 .02180 16.0000 1.1695 .02400 17.0000 1.1550 ●1200O 18.0000 1.1383 .23800 20.0000 1.1172 .28200 22.0000 1.1127 .3290
0 2500000 1.1468 .4050
0 30.0000 ./3550 .5700
0 3500000 .!3800 .74500 40.0000 100350 .92000 45.0000 100500 1.07500 50.0000 100200 10215O0 55.0000 .9550 1.34500 60.0000 .8750 1.47000 65.0000 .7600 1.57500 70.0000 .5300 1.66500 75.0000 .5000 1073500 80-0000 .3650—. 1.7800
49
Table 4. (cent)
O 85-0000 s2300 1.8000.
0 90.0000 .0900 1.80000 95.0000 -.0500 1.78000 100.0000 -.1850 1.75000 105.0000 --3200 1.70000 110.0000 -.4500 1.63500 11500000
●
-.5750 1.55500 120.0000 --6700 1.46500 125.0000 --7600 1.3500 ,
0 130.0000 -.8500 1-22500 135.0000 -.9300 1-08500 140.0000 -.3800 ,92500 145.0000 -.9000 .75500 150.0000 -.7700 .57500 155.0000 -m6700 ●4200O 160s0000 -=6350 .32000 165-0000 -.6800 -23000 170.0000 -08500 .14000 175.0000 -.6600 .05501 180.0000 000000 .0250
5000000.0 NACA 0018 SECTION OATA9 EPPLER P103ELt C.s CDSo
JAN 790.0000 000000 ●0073
o 100000 ●1100 .00730 2.0000 .2200 .007!5o 3.0000 .3300 .00770 4.0000 .4400 .00790 5.0000 .5500 -00830 5.0000 96600 .00870 7.0000 .7700 .00930 8.0000 ● 8538 .01000 9.0000 ● 9525 ●O1O8o 10.0000 1.0404 .01170 11.0000 1.1211 .01280 12.0000 1-1884 .01400 13.0000 1.2430 .01530 14.0000 102808 .01680 1500000 1.3004 .0185
.
@ 1600000 103067 .02030 17.0000 1.3038 -0223 ao 18.0000 1.2960 .02440 1900000 1.2853 .14000 20.0000 1.2768 -28200 22.0000 1.2714 s3290o 25.0000 1.2925 .40500 30.000!I .!3550 .57000 35.0000 .9800 .74500 40.0000 1.0350 *9200o 45.0000 1.0500 1.07500 50.0000 1.0200 1021500 55.0000 .’3550 1.3450
50
Table 4. (cent)
o 60.0000 .8750 1.47000 65.0000 .7600 1.5750
0 70.0000 .6300 1.66500 7!5.0000 ●5000 1.7350
0 80.0000 .3650 1.78001) 8!5.0000 .2300 1.80000 913.0000 .0900 1.80000 9!5.0000 -.0500 1.7800
0 10 I). OOOO -.1850 1.75000 105.0000 -.3200 107000
0 11000000 -.4500 10635O0 115.0000 -*5756 1.5550
0 12000000 -.6700 1046500 125.0000 -.7600 1.3500
0 130.0000 -.8500 1.2250
0 131i. C?OOO -.9300 .1.0850
c1 140.0000 -.9800 .?250
O 145.0000 -.9000 .7550
0 150.0000 -.7700 .5750
0 153.0000 -.6700 .4200
0 16(1.0000 -.6350 .32000 1S5.0000 -*6800 .23000 170.0000 -.8500 .14000 175.0000 -.6500 .0550
2 180.0000 0.0000 .0250
51
Table 5. Lift and Drag Coefficients for the NACA- 0021 Airfoil (104 s Re s 5 x 106)
Re
1000O*O NACA 0021 SECTION DATA~ EPPLER MOJEL~ CLS CDS JAN 79
a CL cd
o 0.0000 0.0000 .04130 1.0000 -.0320 .0414
.
0 2.0000 -.0631 .04200 3.0000 -.0854 .0429
*
o 4.0000 -.0995 .04410 5.0000 -.1156 .0459
0 6.0000 -.1240 .04800 7.0000 -.1400 .05070 800000 -.1475 .05380 9.0000 -.1581 .05750 10* OOOO ‘.1581 .07500 1200000 -.1276 .12300 14.0000 -.0658 .15800 16.0000 s0123 .19600 18.0000 .1035 .23800 20.0000 .2006 .28200 22.0000 .3002 .32900 25.0000 ● 4539 .40500 30.0000 .8550 .57000 35.0000 .9800 .74500 40.0000 1.0350 .9200
0 45.0000 100500 1.07500 50.0000 100200 1.21500 5500000 .9550 1.34500 60.0000 .8750 1.47000 65.0000 .7600 1057500 70.0000 .6300 1.6650
0 7500000 .5000 1.73500 80.0000 .3650 1.78000 8500000 .2300 1080000 90.0000 .0900 1.8000
,
0 95.0000 -.0500 1.78000 100.0000 -.1850 1.75000 10500000 -.3200 1.7000
2
0 110.0000 -.4500 10635O0 115.0000 -.5750 1.55500 120.0000 -.6700 10465O0 125.0000 -.7600 1.35000 130.0000 -.8500 1.22500 13!5.0000 -.9300 1008500 140.0000 -.9800 .92500 14500000 -.9000 .75500 15000000 -.7700 .57500 155.0000 -.6700 .42000 160.0000 -06350 .3200
52”
Table 15.(cent)
O 165.0000 -.6800 .23000 170.0000 -.8500 .14000 175.0000 -.6600 .05501 180.0000 0.0000 ●0250
20000.0 NACA 0021 SECTION DATA* EPPLER M03ELt CL? CDS JAN 790 0.0000 0.0000 .03090 1.0000 .0243 .03100 2.0000 .0393 .03140 3.0000 .0472 .03210 4.0000 .0619 .0352
.0505 .0345: :::;::
●047.5 .03620 7.0000 .0266 .03820 8.0000 .0120 .04070 900000 -.0190 .04350 1000000 -00506 907000 1200000 -.0713 .12300 1400000 -.0362 .15800 16s0000 .0331 .19600 1800000 ●1180 ●2380o 20.0000 .2124 .2820
0 22.0000 .3103 .32900 25.0000 .4618 .4050
0 30.0000 .8550 .57000 35.0000 .9800 .74500 40.0000 100350 .92000 45.0000 1.0!500 1.07500 50.0000 1.0200 1.21500 55.0000 .9550 1.34500 60.0000 ●3750 1.4700
0 65.0000 .7600 1.57500 70.0000 96300 1.66500 75.0000 .5000 1.73500 80.0000 ●3650 1.78000 8’5.0000 .2300 1.80000 90.0000 .0900 1.80000 95.0000 -.0500 1.78000 100.0000 -.1850 1.75000 10’5.0000 -.3200 1070000 110.0000 -.4500 1.63500 115.0000 -.5750 1.55500 120.0000 -.6700 1.46500 125.0000 -.7600 1.35000 130.0000 -.8500 1.2250
0 135.0000 -.9300 1.0850—
o 140.0000 -.9800 .9250
0 14500000—
-09000 .75500 150.0000 -.7700 .5750
0 15’5.0000 -.6700 .42000 16090000 -.6350 .3200 —.
53
Table 5. (cent)
o 16500000 -.6800 .23000 170.0000 -.8500 .1400
0 175.0000 -03300 .05?591 180.0000 0.0000 .0250
40000.0 NACA oo21 SECTION II ATAs E,PPLEq IYODELS CLS CDy JAN 790 0.0000 0.0000 .0232 ,
0 100000 .0752 .02330 2.0000 .1465 .0237
0 300000 ●2103 .0243.
0 4.0000 .2730 .02530 5.0000 ..3086 .0264
0 5.0000 .3382 .02790 7.0000 .3427 .02970 8.0000 .3420 .03.19
0 9.0000 .3162 .03430 10.0000 -2691 .06200 12.0000 .1660 .1230
0 14.0000 .9833 .15800 15.0000 .0981 .19600 18* OOOJ .1619 ●2380
o 20.0000 .2414 s2820o 22.0000 .3345 ,32’300 25.0000 .4802 .4050
0 3000000 .8550 ●5700
o 35.0000 .3800 .74500 40.000C 1.0350 .920!Io 45.0000 1.0500 1.0750
0 50.0000 1.0200 1.21500 55.0000 ● 3550 1.3450
0 60.000il .8750 1.47000 65.0000 .7600 1.57500 70.0000 .5300 1.66500 75.0000 05000 1073500 80.0000 .3650 1.78000 85.0000 .2300 1.80000 90.0000 .0900 188000
“o 95.0000 -.0500 1.78000 100.0000 -.1s50 1.751J0o 105.0000 -.3200 1.7000 x
o 11O*OOOO -.4500 1.63500 115.0000 -*3750 1.!5550o 120.0000 -.6700 1.46500 125.0000 -.7600 1.35000 130.0000 -08500 1.22500 135.0000 -.9300 1.08500 140.0000 -.3800 .92500 145.0000 -.9000 .75500 150.00000 155.0000
0 160s0000
-.7700 .5750‘.6700 .4200-.6350 ●3200
54
Table !5.(cent)
O 16’5.0000 ‘-=5800 .23~0
o 170.0000 -.8500 .14000 17’5.0000 -.6600 *c155~
1 180.0000 0.0000 .025081000fJ.lJ NACA 0021 SECTION OATA? EPPLER M03ELt C.J C)s JAN 79
0 0.0000 0.0000 .017?o ‘1.0000 .9921 .01780 200000 .1839 .Olfllo ,3.0000 .2731 .01860 ‘400000 .3564 .01?4o j.000u .432+ .02040 1; .0000 ●4953 .0217
0 ‘7.0000 ● 5445 .02330 3.0000 ●5751 .02520 ‘900000 .5874 .0273
0 lil.0000 .5780 .0297
0 11.0000 ●5564 .07000 1,2.0000 ● 5228 .12300 1’%00000 .4296 ●1580o 16.0000 ● 3459 .19600 113.0000 .3221 .2380
0 211.0000 *3475 .2820
0 2:2.0003 84091 .32950 25.0000 ●5297 .4050
0 3000000 .3550 .5700
0 33.0000 .3900 .74500 413.00011 1.0350 .92000 4’5.000d 1.0’500 1.07500 50.0000 1.0200 1.21500 55.0000 .3550 1.34500 60.0000 .3750 1*4700o 5500000 .7600 “1.5750o 71j*ogoo .5.300 1.66500 7!3.0000 *’5000 1.7350
0 80.0000 .3650 1.78000 85.0000 .2300 1.8000
0 9(1.0000 .0900 1.8000
0 95.0000 -.0500 1.78E0o 100.0000 -.1850 1.75300 105.0000 -.3200 1.7000
0 11000000 -.4500 1.63500 115.0000 -.5750 1.55500 12[1.0000 -.6700 1.465110 l~j*o(j(Jo -.760C1 1935000 13!1.0000 -.3500 1.22500 13:5.0000 -.3300 1.08500 140*UOQ0 -.9800 .92500 145.0000 -.3000 .7550
(1 15(1.0000 -.7700 .5750
0 15!5.0000 -.670G .4200
55
Table 5. (cent)
O 160.0000 -06350 .3200
0 165.0000 -.6800 .23000 17000000 -.8500 *1400o 175.0000 -.6600 .05501 180.0000 0.0000 .0250
160000.0 NACA 0021 SECTION DATAs EPPLER MOJELS CLt CO* JAN 790 0.0000 000000
*.0139
0 100000 .0842 ●0140o 2.0000 .1879 .0143 .
0 3.0000 .2861 .01480 4.0000 .3800 .01550 5.0000 .4687 .02630 !3.0000 ●5486 .01740 7.0000 .6209 .01870 ,8.0000 .6745 .02040 900000 .7148 .02220 10.0000 ●7374 .0243
—
o 11.0000 ●7443 .02660 12.0000 .7363 .02920 1300000 .7255 .08600 14.0000 ●6993 .1580 “o 16.0000 .6487 .19600 18.0000 .6098 .23800 20.0000 .5920 .28200 22.0000 .5023 .32900 25.0000 .6664 .40500 30.0000 .8550 .57000 3500000 .9800 .74500 40.0000 100350 .92000 4500000 1.0500 1007500 50.0000 1.0200 1*2150o 55.0000 .9550 1.34500 60.0000 -8750 1.47000 65.0000 .7600 1.57500 7000000 .6300 1066500 75.0000 ●5000 1073500 80.0000 .3650 1.7800
,
0 85.0000 .2300 1.80000 90.0000 .0900 1.80000 95.0000 -.0500
%1.7800
0 10000000 -.1850 1975000 105*OOOO -.3200 1.70000 110.0000 -04500 1.63500 115.0000 -.5750 1.55500 12000000 -.6700 1.46500 125.0000 -.7600 1.35000 130.0000 -.8500 1.22500 135.0000 -.3300 1.08500 14090000 ● -.9800 .92500 145.0000 -.9000 .7550
56
Table 5. (cent)
o 150.0000 -.7700 .5750 ‘-’-
0 155.0000 -.6700 .42000 160.0000 -.6350 .32000 165.0000 -.6800 .23000 170.0000 -.8500 .14000 175.0000 -.5600 .05501 180.0000 0.0000 .0250
360000.0 NACA 0021 SECTION DATAs EPPLER M09ELt CLS CDS JAN 790 0.0000 0.0000 .0111
0 1.0000 .1100 .01110 2.0000 .2200 .01130 3.0000 .3024 .01170 ‘4.0000 .4044 .0122
0 5.0000 .4998 .01290 6.0000 .5891 .0138
0 7.0000 .6728 .01490 9.0000 .7434 .0163
0 ‘9*0000 .8026 ●0178o 10.0000 .8500 .0195
0 1100000 .8779 .02150 1:2.0000 .8938 .02370 13.0000 .8973 .02600 1’$.0.000 .8937 .0286
0 1!5.0000 .8840 ●104Oo 16.0000 ●8717 .1960
0 11300000 .8489 .2380
0 213.0000 .8397 .2820
0 z:~.000o .8453 .32900 2!5.0000 .8866 .4050
0 30.0000 .8550 .57000 3!5.0000 .9800 .7450
0 40.0000 1.0350 .92000 45.0000 1.0500 1.0750
0 5(1.0000 1.0200 1.2150
0 55.0000 .9550 1.3450
0 60.0000 .8750 1.4700
0 65.0000 .7600 1.5750
0 70.0000 .6300 1.6650
0 7500000 .5000 1.7350
0 8(1.0000 .3650 1.7800
0 85.0000 .2300 108000
0 90.0000 .0900 1.8000
0 95.0000 -.0500 1.7800
0 10(1.0000 -.1850 1.75000 105.0000 -.3200 1070000 11O*OOOO -.4500 1.6350
0 115.0000 -.5750 1.5550
0 120.0000 -.6700 1.4650
0 125.0000 -.7600 1.3500
0 13[)00000 -.8500 1.2250.
57
Table 5. (cent)
o 13500000 -.9300 “1.0850o 140.0000 -.9800 .9250
0 145.0000 -.9000 .7!550
o 15000000 -.7700 .57530 155.0000 -06700 .4200
0 160.0000 -.63!50 .3200
0 165.0000.
-.6800 .2300
0 17000000 -08500 .14000 175.0000 -.6600 .0550 .
1 180.0000 0.0009 .0250700000.0 NACA 0021 SECTION DATAt EPPLER l’103ELt CL? CDS JAN 79
0 0.0000 0.0000 .00940 100000 .1100 .00940 2.0000 .2200 .00960 3.0000 .3300 .00980 9.0000 .4128 .01030 5.00!30 .5146 .01090 300000 .s100 .01.170 7.0000 ● 6988 .01260 8.0000 .7802 .01.380 3.0000 ●8493 .01520 10.0000 .9091 .01650 11.0000 .9543 .01840 12.0000 .9843 .02020 13.0000 1.0020 .02230 1400000 100122 .02440 13.0000 1.0105 .02690 16.0000 1s0056 .02950 17.0000 .9973 .12500 18.0000 .9911 .23800 20.0009 .9858 .28200 2200000 ●9940 .32300 25.0000 1.3350 .40500 30.0000 .8550 .57000 35.0000 .9800 .74500 40.0000 100350 .92000 45.0000 1.050G 1.0750
,
0’ 50.0000 100200 1021500 55.0000 s 9550 1.3450 *
o 50.0000 .!3750 1.47000 65.000il .7600 1.57500 70.0000 .6300 1.66500 75.0000 85000 .1.73500 80.0000 .3650 1.780Fo 85.0000 .2300 1.80000 90.0000 .0900 1080000 95.0003 -.0509 1.78000 100.0000 -.1850 1.75000 105.0000 –-.3200 1.70000 110.0000 -.4500 1-6350 -.
58
Table 5. (cent)
o 11.5.0000 -.5750 1.5550- “- ‘-
0 1;!0.0000 -.6700 1.4650
0 1:!5.0000 -.7600 1.3500
0 l:sO .0000 -.3500 1.2250
0 135*0000 -.3300 1.0850
0 14}0.0000 -.3800 .9250
0 14} ’5.0000 -.9000 .7550
0 150.0000 -.7700 .5750
0 155.0000 -.670il .4200
0 160.0000 -.6350 .3200
0 165.0000 -.6!300 .2300
0 170.0000 -.!3!500 .1400
0 175.0000 -.6600 .0550
1 18000000 0.0000 .0250
100000000 NACA 0021 SECTION DATA~ EPPLER !103ELs C-a CDS JAN 790 0.0000 0.0000 ●0089
o 1.0000 .1100 .0089
0 2.0000 *~~fJo .0090
0 3.0000 .3300 .0092.
0 4.0000 .4400 .0096
0 500000 ●5192 .0101
0 5.0000 ●61’91 .0108
0 7.0000 .7102 .01170 !3.0000 .7939 *ol~8
o 9.0000 ,869f+ .01400 1,0.0000 .9364 .01540 1.100000 ● 3862 ?0170o 1,2.0000 1.0257 .0187
0 1.3.0000 1.J492 .0206
0 14.0000 1.0657 .0226
0 1.5.0000 1.0709 .0248
0 1,5.0000 1.0690 .02730 1.7.0000 1.0641 .0300
0 19.0000 1-0588 .1350
T7?OOOOO0 1.0554 .2820
0 2!2*OOO0 1.c1644 .32’30
a 25.0000 1.1018 .4050
0 30.0000 88550 .5700
0 35.0000 .9800 .7450
0 4}0.0003 1.0350 s92flfl
o 4}5*0000 1.05T0 1.0750
0 5000000 1.0200 1.2150
0 55.0000 .’3550 1.3450
0 00.0000 .8750 1.47000 f)s.oo~tl .7600 1.575!)
o 70.0000 .G30U 1.665Q
o 75.0000 .5000 1.7350
0 80.0000 .3550 1.7809
0 85.0000 .23U0 1.3036
0 90.0000 .9900 1.8000
Table 5. (cent)
o 95.0000 ‘.0500 1“.7800
o 100* OOOO -.1850 1.75000 105.0000 -.3200 1.70000 11000000 -.4500 1.63500 115.0000 -.5750 1.55500 120.0000 -.6700 1.4650
.
0 125.0000 -.7600 1.35000 130,00000 -.8500 1.22500 135.0000 -.9300 1.0850
“
o 140.0000 -.9800 .9250
0 145.0000 -.9000 .75500 150.0000 -.7700 .57500 15s.0000 -*6700 .42000 16000000 -.6350 .32000 165.0000 -.6800 .23000 170.0000 -.8500 .14000 175.0000 -.6600 .0550
1 180.0000 0.0000 .02502000000.0 NACA 0021 SECTION OATAS :PPLER MO]EL, Ck, c), JAN 79
0 0.0000 0.0000 .00820 1.0000 ●11OO .00830 2.0000 .2200 .00840 3.0000 .3300 .00860 4.0000 .4400 .00890 5.0000 .5500 .00920 6.0000 .6268 .00980 7.0000 .7254 .01050 9.0000 .8143 .01140 9.0000 ● 89860
.012410.0000 .9739 .0135
0 1100000 100398 .01480 12.0000 1.0906 .01620 13.0000 1.1305 .01790 14.0000 1.1580 .01960 15.0000 1.1747 .02150 16.0000 1.1823 .0236 .
0 17.0000 1.1824 .02600 18*OOOtl 1.1814 .02850 1900000 1*1797 .1450
*
o 20.0000 1.1812 .28200 22.0000 1.1893 .32900 2500000 1.2230 .40500 3000000 ●9550 .57000 35.0000 .9800 .“7450o 40.0000 1.0350 .92000 43.0000 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 .9550 1.34500 60.0000 98750 1.47000 65.0000 .7600 1.57’50
60
Table 5. (cent)
o 70.0000 .6300 1.66500 75.0000 .5000 1.7350
0 8000000 ● 3650 1.7800
0 85.0000 .2300 1.80000 90.0000 .0900 108000
0 9’5.0000 -.0500 1.7800
0 100.0000 -.1850 1.75000 105.0000 -.3200 1.7000
0 110.0000 -.4500 1.6350
0 115.0000 -.5750 1.5550
0 120.0000 -.6700 1.4650 -
0 125s0000 --7600 1*350U
o 13000000 --8500 10225O
0 1315.0000 -.9300 1.08500 140.0000 -.9800 .9250
0 14500000 -.3000 .7550
0 150.0000 -.7100 .5750
0 155.0000 -.6700 .+200
O 160.0000 -.6350 .3200
0 165.0000 -.6800 .2300
0 170.0000 -.8500 .1400
0 175.0000 -.6600 .0550
1 180.0000 0.0000 .0250
500000000 NACA 0021 SECTION DATA~ EPPLE3 140DELs CLS C3~ JAN 79
0 0.0000 0.0000 .0078
0 100000 ●11OO .0078
il 2.0000 .2200 .0079
0 300000 .3300 .0081
0 4.0000 .4400 .0083
0 5.0000 .5500 .0086
0 6.0000 .6600 .0091
0 7.0000 .7354 .00970 8.0000 .8334 .0104
0 9.0000 .9222 .0112
0 10.0000 1.0049 .I)121
o 1100000 1.0787 .0132
0 12.0000 1.1453 .0143
0 13.0000 1.1979 .0156
0 14.0000 1.2410 ●017C
o 1500000 1.2680 .0186
0 16.0000 1.2860 .0205
0 17.0000 1.2977 .0224
0 18.0000 1.3031 .0245
0 1900000 1.3066 .0268
0 2!O*OOO0 1.3054 .0273
0 2!200000 1.3130 .3290
0 :!5*OOO0 1.3476 .4050
0 30.0000 .8550 .5700
0 3500000 .9800 .7450
0 40*0000 1.0350 .9200——
61
Table 5. (cent)
o 4!5.0000 1.0’500” i0”07500 50.0000 1.0200 1.21500 55.0000 .95!50 1.34500 60.0000 .8750 1.47009 65e OOO0 .7600 1.57500 70.0000 .6300 1.66500 75.0000 ●5000 1.7350
*
o 80.0000 .3650 1.78000 85.0000 .2300 1.80000 90.0000
*.0900 1.800C
o 95.0000 -.0500 1.78000 100* OOOO -.1850 1.75000 10590000 -.3200 1.70000 110.0000 -.4500 1.63500 115.0000 -05750 1.55500 120.0000 -.5700 1-46500 125.0000 -.7600 1.35000 130.0000 -.8500 1.22500 13500000 -.9300 1.08500 140.0000 --3800 ●9250o 145.0000 -.9000 .75500 150.0000 -.7700 .57500 155.0000 -.6700 .42000 160.0000 -.5350 .32000 165-0000 -.6800 ●2300o 170.0000 -,8500 .14000 175.0000 --6600 .05502 180s0000 090000 ●fj25f’j
62
Table 6. Lift and Drag Coefficients for the NACA10025 Airfoil (104 s Re s 5 x 10G)
Re
Y.OOOo. o VACA 0025 SZCTION DATA~ EPPLER M03ELt C.s CD~ JAN 79
c1 C2cd
o 0.0000 0.0000 .0455
0 ‘1.0000 -.0434 40457
0 2.0000 -.0907 .0453
0 3.00!)0 -.1151 .0474c1 4.0000 -.1403 .04830 5.0000 -.1585 .05080 5.0000 -*1723 .0532
0“ 7.0000 -*1799 .0562Cl 3.0000 -*1797 .05370 3.0000 -.1776 .06380 10.0000 -.1747 .06860 11.0000 -.1647 .082G
o 12.0000 -*1512 .12300 14.0000 -.1134 .15800 15.0000 -. Q60+ .19500 1!3. !3000 .0082 .23!30
o 20*lIooo .0883 .28200 22.0000 .1785 .32900 2.5.0000 .3205 .4050
0 3i1.000o .8550 .5700
0 35.0000 .9800 .7450
0 40.0000 1.0350 .92000 45.0000 1.0500 1.07500 50.0900 1.0208 1.2150
0 55.0000 •~~~o 1.34500 60.000”0 .875Q 1.47000 65.000~ .7600 1.57500 713*oooo .G300 1.66500 75.0000 ●5000 1973500 80.0000 .3650 1.78000 85.0000 .2300 1.80000 90.0000 .0900 1.80000 9500000 -.0500 1.78000 100.0000 -.1850 1.75000 105.0000 -.3200 l*70floo 110.0000 -.4300 1.63500 115.0000 -.5750 1.55500 120.0000 -.5700 1.46500 125.0000 -.7600 1.35600 130.0000 -.3500 1.22500 135.0000 -.9300 1.08500 140.0000 -99800 .9250
0 145.0000 -.9000 .7550
0 150.0000 -.7700 .5750
0 155.0000 __:_.6700 .4200 _
Table 6. (cent)
O 160.0000” --6350 .32000 165.0000 -.6800 s23i10o 170.0000 -.8500 .14000 175.0000 -.6600 .05501 180.0000 0.0000 .0250
2000000 NACA 0025 SECTION C)ATAt EPPLER tlOIELS C_S CDS JAN 79*
o 0.0000 000000 .03410 100000 -.0223 .03+2o 2.0000 -00376 .0346
.
0 3.0000 -.0509 .0354
0 4.0000 -.0550 .03650 5.0000 -.0589 .03790 !5.0000 -.0650 .03970 7.0000 -00690 .04190 8cOOO0 -.0683 .04450 9.0000 -.0653 .0476
0 1000000 -.0635 .05110 11.0000 -.0607 .08100 1200000 -.0572 .1230
0 14.0000 -.0377 .15800 16.0000 -.0027 .19600 18.0000 .0512 .23800 2000000 .1213 .28200 22.0000 ●2071 .32900 25.0000 .3435 .40500 3000000 .8550 .57000 3500000 .9800 .74500 40.0000 1.0350 .92000 45.0000 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 .9550 1034500 60.0000 .8750 1.47000 65.0000 .7600 1.57500 70.0000 .s300 1.66500 75.0000 .5000 1.73500 80.0000 .3650 1.7800 +
o 85.0000 .2300 1.80000 90.0000 .0900 1.80000 95.0000 -.0500 1.7800 >
0 100.0000 -.1850 1.75000 105.0000 -.3200 1.70000 11090000 -.4500 1.63500 115.0000 -.5750 1.55500 120.0000 -.6700 1.46500 125.0000 -.7600 1.35000 13090000 -.B500 10225O0 135.0000 -.9300 1.08500 140.0000 -.9800 .92500 145.0000 -.9000 .75500 15000000 -.7700 .5750
64
Table 6. (cent)
o 155.0000 -.”6700 .42000 1610.0000 -.6350 .32000 165.0000 -.6800 .23000 17’000000 -.8500 .14000 115.0000 -.6600 .05501 1(30.0000 0.0000 .0250
40000.0 YACA 0025 SECTION DATAs SPPLER F103ELs CLS C3S JAN 790 0.0000 0.0000 .02580 1.0000 ●0*11 .02590 2.0000 .0821 .02630 3.0000 .1167 .0269
0 4.0000 .1479 .02780 5.0000 ●1693 ●0290o 5.0000 .1778 .030+o 7.0000 ●1856 -03220 800000 ● 1929 .03430 9.0000 .1942 .03670 10.0000 ●1915 .03960 11.0000 .1889 .04280 12.0000 .1813 .08500 1$00000 ●1753 .15800 16.0000 .1669 .19600 1800000 .1824 .23800 2000000 .2183 .28200 22.0000 .2843 .32900 25.0000 .4026 .40500 30.0000 .!3550 .57000 35.0000 .9800 .7450
0 40.0000 1.0350 .9200
0 45.0000 1.0500 1907500 50.0000 100200 1.21500 55.0000 .9550 1.34500 60.0000 .8750 1.47000 65.0000 m7600 1.57500 70.0000 .6300 1.66500 75.0000 .5000 1.7350 .0 80-0000 -3650 1-78000 85.0000, .2300 1.8000
0 90.0000 .0900 1.80000 95.0000 -.0500 1.78000 100*OOOO ‘.1850 1.75000 105.0000 -.3200 1.70000 11000000 -.4500 1.63!50o 115.0000 -.5750 ‘ 1.55500 120.0000 -.6700 1.46500 125.0000 -.7600 1.35000 130.0000 -.8500 1.22500 135.0000 -.3300 1.08500 140.0000 -.9800 .9250
—
o 145.0000 -.9000 .7550
65
Table 6. (cent)
o 150.0000 -.7700 .57500 155.0000 -.6700 .42000 160.0000 -.6350 .3200II 155.0000 -96800 ●2300o 170.0000 -.8500 .14000 175.0000 -.6500 *0550 e
1 180eOOO0 0.0000 .025080000.0 NACA 002’3 SECTION OATA~ ZPPLER t103ELs Cl? C3S JAN 79
0 0.0000 0.0000 .0197 ,,
0 1.000?) .0743 .01980 2.0000 .1487 .02010 3.0000 .2198 .02070 4.0000 .28.32 .02140 500000 ●3413 .02240 6.0000 .3866 .02360 7.0000 .4215 .02500 8.0000 .4503 .02680 9.0000 .465’5 .02380 10.0000 .4749 .03110 1100000 .%797 .03380 12.0000 .~?83 .03680 1300000 .4754 .04010 1%.0000 .4713 *1OLOo 1600000 -4588 .19600 18.0000 .4522 ●2380o 20.0009 *4547 .28280 22.0000 ●*826 .32900 25.0000 95574 ●4050
o 30.0000 .:3550 .57000 33*OCO0 .9800 .74500 411.000cl 1.0350 .92000 45.0000 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 *9550 1.34500 50.0000 .d750 1.47000 65.0000 ●7600 1.57500 70.0000
%●6300 1.6650
d 75.0000 ●5000 1.73500 80.0000 W3550 1.7800 >0 85.0000 .2.300 1.80000 90.0000 .0900 1.80000 93.0008 -.0500 1.78000 100.0000 -.1850 1.75000 105.0000 -.3200 1.70000 Ilo.000fl -.4300 1.63500 115.0000 --5750 1.55500 120.0009 -.6?00 1.46500 125.0000 -.1600 1.35000 130.000!I -.8500 1.22500 135.0000 -.9300 1.0850
Table 6. (cent)
o 14000000 ‘.9800 .92500 145.0000 -.9000 .75500 150.0000 -.7700 .57500 155(.0000 -.6700 .42000 16000000 -.6350 .32000 155’.0000 -*&800 .23000 170’,0000 -* B500 .14000 175!,0000 -.6500 .0550
1 180100000 000000 ●0250160000.0 NACA 0025 SECTION I)ATAs EPPLER F40DEI-, c~, c)), JAN 79
0 0{00000 0.0000 .01!5!5o l!BOOOD .0375 .0156
0 2’00000 e 1745 .0158
0 3(,0000 .2613 .0163
G ~mtlooo .3$%00 .01690 5(,0000 .4170 .0177
0 6!,0000 .4831 .01870 74,0000 .5263 .02010 81,0000 .5916 .02130 9,,0000 .6271 .02300 10!DOOOO .6539 .02500 11(,0000 .6720 .02720 12!)0000 .6811 .0236f) 13{00000 ●6866 .03240 14’00000 .6886 .03s5o 151,0000 .6906 .03890 1s{.0000 .6321 .04260 17!.0000 ●6935 .04660 18.0000 *6945 .05100 19!.0000 .7006 .05580 2000000 .7069 .06100 21moooo .7164 .06680 224BOOO0 .7289 .0730
0 ‘23s0000 .7421 .079$5
0 244)0000 .7605 .087fl
o 25<,0000 .7840 .09470 26!.0000 .8047 .1029
0 27,0000 .8306 .1117
0 3otBoooil .3550 .5700
0 354s0000 .9800 .7450
0 40,.0000 1.0350 .9200
0 454.0000 1.0500 1907500 504,0000 1.0200 1.2150
0 5500000 * 9550 1.3450
0 60,mOOO0 .8750 1.4700
0 654.00IJO .7600 1.57500 70,.0000 .5300 1.6650
0 75(.0000 ●5000 1.7350
0 80mOOO0 .3650 1.7800
0 85400000 .2300 1.8000—
67
Table 6. (cOnt)
o 90.0”000 .0900 1.80000 95.0000 -.0500 1.7800
0 10000000 -.1850 1.75000 105* OOOO -s3200 1070000 110.0000 -.4500 1.63500 11!5.0000 -.5750 1.55500 120.0000 -.6700 1.4650
a
O 12500000 -.7600 1.35000 130.0000 -.8500 1.2250 ,
0 13s.0000 -09300 1.08500 140.0000 -.9800 .92500 145.0000 -09000 .75500 150.0000 -.7700 957500 155.0000 -.6700 .42000 160.0000 -.6350 .32000 165.0000 -.6800 .23000 170.0000 -.8500 ●1400o 175.0000 -.6600 .05501 180.0000 0.0000 .0250
360000.0 NACA 0025 SECTION DATA~ SPPLER MO)ELS CLS C3S JAN 790 000000 000000 .01210 1.0000 .0982 .01220 2.0000 .1721 .01250 3.0000 .2682 .01290 4.0000 .3608 .01350 5.0000 ●4495 .01410 6.0000 .5295 .01490 7.0000 .6062 .01590 8.0000 .6701 .01700 9.0000 .7256 .01850 10.0000 .7713 .02000 1100000 .8039 .02190 1200000 ,8295 .02390 13.0000 ● 8471 ●0261o 14.0000 .8565 .02860 15.0000 .8656 .03140 1600000 ●8742 .03430 17.0000 ● 8821 .03750 18.0000 .8890 .04110 19.0000 ● 8992 .04480 20.0000 .9114 .04890 21.0000 .9216 .05340 22.0000 .9381 .05820 2300000 .9529 .063+O 24.0000 .9721 .06900 2500000 .9907 .07500 26.0000 100147 .08140 27.0000 1.0396 .08810 30.0000 .8550 .5700
.
o 35.0000 .9800 .7450
68
Table 6. (cent)
o 40.0000 1.0350 .92000 45.0000 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 ● 9550 1.34500 60.0000 .8750 1.47000 65.0000 .7600 1057500 70.0000 .6300 1.66500 75.0000 .5000 1.73500 80.0000 .3650 1.78000 85.0000 ●2300 1.80000 90.0000 .0900 1.80000 95.0000 -.0500 1.78000 100.0000 -.1850 1.75000 105.0000 -.3200 1.70000 110.0000 -.4500 lm6350
o 11500000 -.5750 1055500 120.0000 -.6700 1.46500 125.0000 -.7600 1.35000 130.0000 -.8500 1.22500 135.0000 -.9300 1.0850
0 140.0000 -.9800 .92500 145.0000 -.9000 .75500 150.0000 -.7700 .57500 155.0000 -.6700 .4200
0 160.0000 -.6350 .32000 165.0000 -.6800 .23000 170.0000 -.8500 .14000 175.0000 -.6600 .0550
1 18000000 0.0000 .0250700000.0 NACA 0025 SECTION DAIAt E?PLER M03EL9 CL* CD9 JAN 79
0 0.0000 0.0000 .01040 1.0000 .0817 .0104
0 2.0000 .1851 ●0105o 3.0000 .2861 .0109
0 4.0000 .3811 .01130 5.0000 .*743 .01190 6.0000 .5627 .01260 7.0000 .6440 .0134
0 8.0000 ●7194 .01440 9.0000 .7852 .0156
0 1000000 .8405 .01700 11.0000 .8873 .01850 12.0000 .9230 .02020 13.0000 .9491 .0222
0 1400000 .9685 .0244
0 15.0000 .9820 .0267
0 16.0000 * 9944 .02920 1700000 1.0052 .03190 18.0000 1.0157 .0349
——
0 19.0000 1.0276 .0381—
69
Table 6. (cent)
o 20.0000 1.0403 .04150 21.0000 1.0521 .04530 2200000 1.0678 .04930 23.0000 1.0831 .05360 24.0000 1.1035 .0583
0 25.0000 1.1223 .0632 t
o 26.0000 1*1458 .06850 27.0000 1.1704 .07410 30.0000 .8550 .5700
.
0 35.0000 .3800 .74500 40.0000 1.0350 .92000 45.0000 1.0500 1.07500 50.0000 1.0200 1.21500 55.0000 ●3!550 1.34500 60.0000 .8750 1.47000 65.0000 .7600 1.57500 70.0000 ● 6300 1.6650
0 75.0000 .5000 1073500 80.0000 .3650 1.78000 85.0000 .2300 1.80000 90.0000 .0900 1.80J0o 9500000 -00500 1.780!)o 100.0000 -.1850 1.’7500
0 105* OOOO -.3200 1070000 110.0000 -.4500 1.63500 11500000 -.5750 1.55500 120.0000 -.6700 1.46500 125.0000 -.7600 1.35000 130.0000 -.8500 1.22500 135.0000 -.9300 1.08500 140.0000 -.9800 .92500 145.0000 -.9000 .75500 150.0000 -.7700 .57500 155.0000 -.6700 .42000 160.0000 -.6350 .32000 165.0000 -.6800 .2300 *
o 170.0000 -.&500 .14000 175.0000 -.6600 .05501 180.0000 0.0000 90250 s
1000000.0 NA:A 0025 SECTION DATA? EPPLER M03EL~ CL? Ca9 JAN 790 0.()()()0 000000 .00970 1.0000 .1100 .00980 2.0000 .1890 .00980 3.0000 .2917 .01010 4.000C .3900 ●0105o 5.0000 .4844 .01100 6.0000 85757 .01160 7.0000 .6622 .01240 8.0000 .7387 001330 9.0000 .8117 .0144
70
Table 6. (cent)
o I1O*OOOO .8710 .0157fl 1.1.0000 .9228 .01710 11240000 ● 3656 .01870 1.300000 .9960 .0205
0 1.4.0000 1.0192 .02250 1.5.0000 1.0382 .0246
0 1.600000 1.0522 e0269o 1.700000 1*0654 .0294
0 18.0000 1.0774 .03221.!3.0000o 1.0896 .0351
0 20*0000 1*1031 .03820 21.0000 1*1151 .0417
0 2200000 1.1294 .04540 :!3.0000 1.1476 .0493
0 24.0000 1.1645 .05350 2!500000 1.1856 .0581
0 :!6.0000 la2071 .0629
0 :!700000 1.2317 .06800 30.0000 .8550 .57000 35.0000 .9800 .74500 4to*ooQo 1.035a .9200
0 ql!j.000o 100500 1.07500 50.0000 1.0200 1.21500 55*0000 .3550 1.3450
0 60.0000 .8750 1.47000 65.0000 .7600 1057500 70.0000 .6300 1.6650
0 7’5.0000 95000 1.73500 810.0000 .3650 1078OO
0 a5*oooo .~30(J 1080000 90.0000 .0900 108OOGo 9’5.0000 -.0500 1078OO0 100.0000 -.1850 1.75000 10’3.0000 -s3200 1.7000
0 11O*OOOO -.4500 1.63500 11500000 -.5750 1055500 120.0000 -.5700 1.46500 12!5.0000 -.7600 1.35000 130.0000 -.8500 1022500 135.0000 -09300 1008500 14000000 -.9800 .925g
o 145.0000 -.9000 .7550
0 150.0000 -.7roo 957500 155.0000 -.6700 .4200
0 150.0000 -.6350 .3200
0 165.0000 -.6800 .2300
0 170.0000 -.3500 .1400
0 175.0000 -.6500 .0550
1 180.0000 0.0000 .0250
2000000.C NACA 0025 SECTION DATA? EPPLER MOIELt CL* CDS JAN 79
71
Table 6. (cent)
—.- ..——0 0.0000 0.0000 .00900 1.0000 .1100 ●0090
0 200000 .2200 .0091
0 3.0000 .2978 .00930 4.0000 .4000 .0096
0 500000 ●4977 .0100 8
0 S.000o .5913 ●01060 7.0000 .6810 .01120 8-0000 .7664 .0120
,
0 900000 .8415 .01290 10.0000 ● 9135 .01400 11.0000 .9723 .0151
0 12.0000 1.0245 .01650 1200000 1.0245 .01650 13.0000 1.0672 .01800 1400000 1.0989 .01970 15.0000 1.1258 .0215
0 16.0000 1.1488 .02350 1700000 101654 +0257o 18.0000 1.1806 .02800 1900000 1.1953 .03050 20.0000 1.2094 .03320 21.0000 1.2220 .03620 22.0000 1.2354 .03940 2300000 1*2537 .04280 2*.0000 1.2683 .04650 2500000 10289O .05040 26.0000 1.3087 .05450 27.0000 1*3347 .05890 30.0000 .8550 .5700
0 35.0000 .9800 .74500 40.0000 1.0350 .92000 45.0000 1.0500 1.07500 5000000 1.0200 10215O0 55.0000 .9550 1.34500 60.0000 .8750 104700 *
O 65.0000 .7600 1.57500 70.0000 .;300 10665O0 75.0000 .5000 1.73500 80.0000 .3650 1078OO0 8500000 .2300 1.80000 90.0000 .0900 1-80000 95.0000 -.0500 1.78000 100.0000 -.1850 1.75000 105.0000 -.3200 1970000 11000000 -.4500 1.63500 115.0000 -.5750 1.55500 120.0000 -.6700 1.46500 125.0000 -.7600 193500
—
o 130.0000 -08500 10225O
72
Table 61.(cent)
o 135.0000 -.9300 1.08500 140.0000 -.9800 .9250
m5*oooo -.9000 .7550
0 15000000 -.7700 .5750
0 15500000 -.6700 ●4200O 160.0000 -.6350 .3200
0 165.0000 ‘.6800 .2300
0 17000000 -.8500 .14000 175.0000 -06600 .0550
1 18000000 0.0000 .02505000000.0 NACA 0025 SECTION DATAs EPPLEI? P103ELs CL? C3S JAN 79
0 000000 000000 .0084
0 1.0000 .1100 .0084
0 2.0000 .2200 .0085
0 ,3.0000 .3300 .0087
0 4*0000 .4078 .0089
0-----!5.0000 .5097 .0092
0 500000 .6076 .0097-7.00000 .6997 90103
/3.0000 ● 7886 .0110
L3.0000 .8730 .01170 10.0000 .9472 .0126
71.00000 1.0177 .0137
0 1290000 1.0750 .0148
0 1:3.0000 1.1270 .0161
0 1’).0000 1.1717 .0175
0 l!i.000o 102065 .0190
0 11500000 1.2358 .0207
=?.0000 1.2617 .02250 18.0000 1.2790 .0245
0 19.0000 1.2952 .02670 2000000 1.3121 .0290
0 211.0000 1.3257 .03160 2200000 1.3378 .0344
0 23.0000 1.3558 .0374
0 24.0000 1.3735 .0404
F-Z5.000o 1.3960 .04360 26.0000 1.+187 .0470
0 2ir*oooo 1.4395 .0509
0 3(1.0000 ,8550 .5700
0 35.0000 .9800 .7450
0 40.0000 1.0350 .9200
0 45.0000 100500 1.07500 5[1.0000 1.0200 1.2150
0 55.0000 ● 9550 1.3450
0 6(1.0000 .8750 1.4700
0 65.0000 .7600 1.5750
0 7[1.0000 .6300 1.6650
0 75.0000 .5000 107350
0 80.0000 .3650 1.7800
73
Table 6. (cent)
o 85.0000 .2300 — 1.8000o 90.0000 .0900 1.8000
0 95.0000 -.0500 1.78000 100* OOOO -.1850 1.75000 105.0000 -.3200 1.70000 110.0000 -.4500 I063!50o 115.0000 -.5750 1.5550
e
O 120.0000 n -.6700 1.46500 125.0000 -.7600 1.3500
0 130.0000 -.8500 1.2250.
0 135.0000 -.9300 1.08500 140.0000 -.9800 ,9250
0 145.0000 -.9000 .7550
0 150.0000 -.7700 .5750
0 155.0000 -.6700 .4200
0 160.0000 -.6350 .32000 165.0000 -.6800 .2300
0 170.0000 -.!3500 .1400
0 175.0000 -.6600 .0550
2 180.0000 0.0000 .0250
74
II
I I II
I I I I I
80 —
G 60’-8a.
$x= 0.5
.g 40~
s
20 —
o80
Rotation Angle, (3(deg)
14020 40 60 100 120 160 180
Figure 1. Equatorial Plane Angle of Attack Variation for the 17-Metre Turbine at a Rotational Speed of 46 rpm (4.82 rad/s)
107/ I I 1 I 1 I I I I I T I I I I I 14
8
6
4
2
tx= 3.()~06 .
8 -
6 -
4 “
2 -
10 1 I 1 I I I 1 I 1 I 1 I 1 i 1 1 1 Io 20 40 60 80 100 120 140 160
Rotation Angle, 0 (deg)
Figure 2. Variation of the Chord Reynolds Number at the Equatorial Plane of the 17-Metre Turbine at a Rotational Speed of 46 rpm (4.82 rad/s)
. . .
NACA-OO09 Airfoil Section
[’“..4
-~4 -~o -16 -12 -8 -4 A 4 8 12 16 20 24
tltttntt
Figure 3. Section Lift Coefficients for the NACA-0009 Airfoil at Reynolds Numbers of 0,36 x 106 and 0.69 x 106
NACA-0012 Airfoil Section
O Increasing Cl
O Decreasing u
-24 -20 -16 -12 -8 -4
Y
.
.
Figure 4. section Lift Coefficients for the NACA-0012 Airfoilat ReynoldsNumbersof 0,36x 106and 0.70x 106
NACA-0012 Airfoil Section
A Increasing ct
E-20 -16 -12 -8 -4 I A 4 8 12 16 20 24 I
Angle of Attack, a (deg)
—. —
\
I
Figure 5. Section Lift Coefficients for the NACA.0012 Airfoil at Reynolds Numbers of 0.86 x 106 and 1.76 x 106
NACA-0012H Airfoil Section
o Increasing a
_ A Increasing o,
-24 -20 -16 -12 -8 -4 12 16 20 24
Angle of Attack, a (deg)A
II
I iw
1II #
- 1.4
Figure 6. Section Lift Coefficients for the NACA-0012H Airfoil at Reynolds Numbers of 0.36 x 106 and 0.70 x 106
.
NACA-0015 Airfoil Section
[: .
.1.4
}
O Increasing a Re = 0.36 x 106
D Decreasing a
}A Increasing Ct Re = f)68 x 106 1.20 Decreasing a)
-24 -20 -16 -12 -8 -4
Angle of Attack, u (deg)
\
Figure 7. Section Lift Coefficients for the NACA-0015 Airfoil at Reynolds Numbers of 0.36 x 106 and 0.68 x 106
81
I I I II
I I I I I I I I I I I I I I1 .4– –
1.2- -NACA-0012H
~~ l.o– -
~“.-
; 0.8- –
;.-~ 0.6- –a
6 NACA-0009 NACA-0012
0 .4– -
0.2- -
1 I t I 1 I t I 1 I t A ,-24 -20 -16 -12 -8 -4 / 4 8 12 16 20 24
—
—
NACA-0009
A /~
-0.4
NACA-0012
— -0.6
— -0.8\\\v
Angle of Attack, a (deg)
i
w NA(7-.O012H-1.2 -
-1.4 –
I I I I 1 I I I 1 I I I I I I I I I I 1 I
Figure t3.Section Lift Coefficients for Four Airfoil Sections at an ApproximateReynoldsNumberof 0.70 x 106
82
1
0
0
-o
-o
-1.0
-1.2
Angle of Attack, a (deg)
Figure 9. Full Range Section Lift Coefficients for the NACA-0009 Airfoil at Reynolds Numbers o f 0.36x 106, 0.50 x 106, and 0.69x 106
,-, II
1
c
-o
-o
-o
-1
-1
Angle of Attack, a (deg)
Figure 10. Full Range Section Lift Coefficients for the NACA-0012 Airfoil at Reynolds Numbem of 0.36 x 106, 0.50 x 106, and 0.70 x 106
“e
G.-Ak0
-2.3~:ko-
$
Angle of Attack, a (deg)
Figure 11. Full Range Section Lift Coefficients for the NACA-0012H Airfoil at Reynolds Numbers of 0.36 x 106, 0.49 x 106, and 0.70 x 106
!1 I I I IH “
#
II I I I I I I I I I I
Iz I II I I I I I IL
I!IIIIIIMI II 1- I I I I I I I I
FEiFFFFG
.:
:(nuMc2
m
,.
86
—f ?
—
—
—
—
—
o m—
o ❑ $1.
00<—
o ❑—I
w
c+
w
d-
-i-t-w’’’’’’m’”i—.0
+j
I 00 a zI 2
WI-i-%llnl”l Allllll~
Hio •1—
g
—
I I I I I 1 I
I I I I I I I I Q wo 0. .
I I
I 1-
A“xmw0II wu
:
30
0 00
0.032 I 7
$
0.028 ‘ ❑R
❑ ~ A
0.024 ❑
2A
y 0.020 k •1- 0
z.3 •1& o B ❑~: 0.016 ,
22
❑
R
o ❑0.012 0
:El
0.008 — ORe = 0.36x 106NACA-0012
i– o– ;Airfoil Section
R
— ❑ Re= 0.50x 106
0.004 “ A Re = 0.70 x 106
0.0 .
-16 -12 -8 -4 0 4 8 12 16 20
Angle of Attack, a (deg)
Figure 14. Section Drag Coefficients for the NACA-0012 Airfoil at Small Angles of Attack and Reynolds Numbers of 0.36 x 106, 0.50x 106, and0.70 x 106
. ●✌ ● ✎
0C4
w
89
0.032
0.028
0.024
~v 0.020
E.3&
~u%’ 0.016’
d
I
0.012
0.008 — ORe = 0.36x 106
❑ Re=O.49x 106
0.004
0.0
4
Elo
n o•1 ~
_ A 0 •1A— — — —
❑ 0 A
A •1 A.00
0
““Af-J A
0n o— A
A❑
NACA - 012H g R A
Airfoil Section
— A Re=O.70x 106
i 4-16 -12 -8 -4 0 4 8 12 16 20
Angle of Attack, a (deg)
Figure 16. Section Drag Coefficients for the NACA-0012H Airfoil at Small Angles of Attack and Reynolds Numbers of 0.36 x 106, 0.49x 106,and 0.70 x 106
. ●
oc-i
m
co
w
oc’!
2.2 ‘
2.0 —~ Re = 0.36 x 106 NACA-0009 Airfoil Section
❑ Re=O.50x 106
1.8ARe=O.70x 106 0
8% Jln AQ:
ooeoa
081.6
A~n o
8 9!!
:1.4”;
~ 8(a% 1.2 I
~.-U 8.- %~ 1.0’ !2u
8°E
0.8
ee8
0.68b t)
50.4
fin6
#
f’ fli0.2- t)
6
0Kl!l@ 6)10 20 30 40 50 60 70 80 90 100
A110 120 130 140 150 160 170 180
Angle of Attack, a (deg)
Figure 18. Full Range Section Drag Coefficients for the NACA-0009 Airfoil at Reynolds Numbers of 0.36 x 106, 0.50 x 106, and 0.69 x 106
e s . .
2.2 ,I
NACA-0012 Airfoil Section2.0
0 Re=O.36x 106❑ Re= ().5()x 106
1.8 — ‘A Re =Oe69x 106 ~~g::o.gg
:
1.6•1A 6
❑ 0 08
OA A~ 1.4u A
❑ 806 A: 1.2 •1 8ko
8°
00
E a
$ 1.0g o
6%u --8°
❑
0.8
f3°6
0.6 - 6~
f3
0.4 .9° Bo
6°0
0.2.[
n
bo
0 ~ Ii n10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180
Angle of Attack, u (deg)
Figure 19. Full Range Section Drag Coefficients for the NACA.0012 Airfoil at Re~nold~ Numbers of 0.36 x 106, 0.50 x 106, and 0.70 x 106
2.2-
2.0 — 0 Re=O$36x 106NACA-0012H Airfoil Section
0 Re=O.49x 106
1.8 — A Re= 0.70x 106 Q $?? 30 d El 8Pi -, •1 !?
1.6’3 3
6 -J2 F
2 1.4 1 g
G
:
b 3
% 1.2Q 3“
jj 2.< c1 3g 1.0 A
G i u
6$
0.8( 3
n0.6. 9 ‘!
t!!
c)0.4 0
6
B-0.2. @
U
(3
0 ~ p a 3 n10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160
Angle of Attack, ~ (deg)170 180
Figure 20. Full Range Section Drag Coefficients for the NACA-OCJIZHAirfoil at Reynolds Numbers Of0.36 x 106, 0,49 x 106,and 0.70 x 106
. * . *
2.2I,
2.0
1.8 – A Re= 0.68x 106I
1.6
1.4
-dug 1.2&%
o.+o.-*~
u 0.8
0.6
0.4El
nh
0.2 n
o&clZm o @ P m
10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180
Angle of Attack, a (deg)
Figure 21. Full Range Section Drag Coefficients forthe NACA-OO15Airfoil at ReynoIds Numbemof 0.36x 106, 0.50x 106,and O.68 x 106
Angle of Attack, u (deg)
Figure 22. NACA-0009 Airfoil Section Moment Coefficients About the Quarter Chord for Reynolds Numbers of 0.36 x 106,0.50 x 106, and 0.69 x 106
96
Angle of Attack, a (deg)
Figure 23. NACA-0012Airfoil Section MomentCoefficients About the QuarterChord for ReynoldsNumbersof 0.36 x 106,0.50 x 106, and 0.70 x 106
97
I I I I I I I
~
I r RI I I
-me= 1.76x 10” I i I I I I I1111
Figure 24. NACA-0012 Airfoil Section Moment Coefficients About the Quarter Chord for Reynolds Numbers of 0.86 x 106,1.36 x 106, and 1.76 x 106
98
Figur(0.49 x
-4
-,
-2
Angle of Attack, a (deg)
! 25. NAC-4-0012HAirfoil Section MomentCoefficients About the QuarterChordfor ReynoldsNumbersof 0106, and 0.70 x 106
.36 X 106,
99
[ I I I [ I I Iu 1
Angle of Attack, a (deg)
Figure 26. NACA-0015 Airfoil Section Moment Coefficients About the Quarter Chord for Reynolds Numbers of 0.36 x 106,0.50 x 106, and 0.68 x 106
100
0.3 I I I I I II
I I I I I I
o Re = 0.36 x 10: NACA-OO09Airfoil Section0.2 ❑ Re =0.50x I()
A Re =0.69x 106
0.1
0.0( A $l@ 20 30 40 50 6f) 7f) 80 90 100 110 120 130 140 150 160I 170 lgo
k –: 5 0 1“~ -0.1
n—
EnAao~
b ~oO- —v~ .0.2 ❑ A r A R“. AOUA ❑ 00 •1
g AA on 1 0 A:2 0 2
AQg -0.3 o
A ; >A As ❑ A o
❑ oRB– ‘:R
z A~ -0.4 0 ;
o d A❑
8 E/o
0$3 ‘E
:4AP
❑
-0.5 0—0 n o0
❑ o
0°0-0.6 0— o
-0.7
Angle of Attack, a (deg)
Figure27. Full RangeSection MomentCoefficientsAboutthe QuarterChordfor the NACA-0009Airfoil at ReynoldsNumbersof 0.36 x 106,0.50 x 106, and 0.69 x 106
.0
0.3 1I I I I
~ Re =0.36x 106I I
NACA-0012 Airfoil Section0.2 ❑ Re= 0.50x 106
~ Re=O.70x 106&
0.1
o—
0.0( A .2 P0
10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 18tiB ,
T n E/0. .E1~ -0.1 ‘ o
“E~lo * ❑
o —o t
$ -0.2 -
--t-
‘A :B
❑
❑A
.+u ❑AU o
.-$ 0 0° >
ARk A8 *P
G .().3A n 8 ❑
A~
A Io A.. A~- A~ JJLt_- _.1.l
f
‘E 0 I•1
5111~_ l!ii -0.4
0-~
ao
r“ ‘r “?
0–0– ~f;
A
-0.5 0 •1 AH r
A c1 A
0
-0.60
-0.7
Angle of Attack, a (deg)
Figure 28. Full Range Section Moment Coefficients About the Quarter Chord for the NACA-0012 Airfoil at Reynolds Numbers of 0.36 x 106,0.50 x 106, and 0.70 x 106
0.3 IllORe=O.36xlo6 NACA-0012H Airfoil Section
0.2❑Re= 0.49x 106,ARe=o.7ox lo6
0.1
$4
f3–
0.0( ).@ n 010 d 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180
❑n E fQ A
?~ -0.1 A To
j A o0 8 A
o
~“ -0.2 Q~ A 0:.-0 ❑
❑ A.+%
on , AAA
~u
AOOO-0.3
❑A 6 o~6— — z1
;0 3 b A.
❑ zl~p A E0
;g -0.4
Ao 0 El ❑ 4
3 0 io❑
OAA
o❑ o o
❑ ~—~—g–a
-0.5 \A t
o A
o ❑
-0.6 r
-0.7
Angle of Attack, cx(deg)
Figure29. Full RangeSectionMomentCoefficientsAboutthe QuarterChordfor the NACA-0012HAirfoil at ReynoldsNumbersof 0.36x 106,0.49 x 106J and 0.70 x 106
f
0.3 II I I I,0 Re = 0.36x 106
1NACA-0015 Airfoil Section
❑ Re = 0.50x 1060.2 A Re = o.68x lo6
0.1 n
f.j~o
Ooi ~ ~ I &10 ‘-’20 30 40 50 60 70 80 90 100 110 120 130 140 150 160 170 180
0 8 $~o 1°‘A
-o.i:Fr
~AD-g A—0 ❑
4.2 oh I AAL o A
❑*– •~ b •~ 0
-0.31
I❑
A ❑galfj
h ❑3
0 ~ 1A— 0
A—L 2 0
-0.4 0 A— o~ A L 6—0 –B –: –~t❑ A 00
1aI
o A— — *— ~L
RIJ?’A o❑
-0.50 0
❑ Q$ A
-0.6 0 L
o
-0.7
+Angle of Attack, a (deg)
Figure 30. Full RangeSection MomentCoefficientsAbout the QuarterChordfor a NACA-0015Airfoil at ReynoldsNumbersof 0.36 x 106,0.50 x 106, and 0.68 x 106
I I I I I I I I I I I I I I I I I I I 1 I I I I I I I 1 1 I I 1 I I I I [ I0.32
0.28
0.24
0.20
0.16
0.12
0.08
0.04
0.0
-0.04
-0.08
-0.12
-0.16Angle of Attack, a (deg)
Figure 31. Full Range Section Axial Force Coefficients for the NACA-0012 Airfoil at Reynolds Numbers of 0,36 x 106, 0.50x 106, and 0.70x 106
0.32
0.28
0.24
0.20
0.16
Angle of Attack, a (deg)
Figure 32. Fu1l Range Section Axial Force Coefficients for the NACA-OOIZH Airfoil at Reynolds Numbers of 0.36 x 106, 0.49x 106, and 0.70 x 106
4? * -1
Angle of Attack, a (deg)
Figure 33. Full Range Section Axial Force Coefficients for the NACA-0015 Airfoil at Reynolds Numbers of 0.36 x 106,0.50x 106, and 0.68x 106
Minimum Drag Coefficient forthe NACA-0015 Airfoil
0.06- 1 1 I I I I I 1 I I I I 1 1 I I 1 I I 1 I II
I I I I I I 1
0 Eppler Data0.05 “
❑ Wichita State U.
~o 0.04 —v.
~.-28 0.03 -
von
~
.[ 0.02 –
J
0.01 –
0.0 1 1 I I I II 1 1 I 1 I I 1 I I 1 I 1 1 I 1 1 1 I I I I I
~04 ~05 106 ~07
Figure 34. Predictedand MeasuredValuesof MinimumSection Drag coefficients, c do,
as a Function of ReynoldsNumber,Re
108
1 I I II I I I I I 1 I I I I I I I I 1 I 1I
I I 1 I I 1 I I
Maximum Lift Coefficientfor the NACA-0015 Airfoil
❑
O Eppler Data
❑ Wichita State U.
i 1 ,,, [,,,,,,,, , ,,,,,,,, , ,,,,,,’
Reynolds Number, Re
Figure 35. Predictedand MeasuredValues of Section MaximumLift Coefficients, c/max‘as a Function of ReynoldsNumber,Re
109
i
110
II
II
II
II
II
1I
II
-.
.0
-.
I1
1I
1I
1I
11
II
1I
Q.
VI
*q
m.
.0.
0+
o“o
00
o“o
0
0a
o
00oa
o0doo
m..0mr-
X
v)*coH0
111
Distribution:TID-4500-R68 UC-60 (326)
Wichita State University (2)Aero Engineering DepartmentWichita, KS 67208Attn: M. Snyder
W. Wentz
Virginia Polytechnic Institute andState University
Department of Engineering Scienceand Mechanics
Blacksburg, VA 24060Attn: R. E. Akins
Assistant Professor
Aluminum Company of America (5)Alcoa LaboratoriesAlcoa Technical CenterAlcoa Center, PA 15069Attn: D. K. Ai
A. G. CraigJ. T. HuangJ. R. JombockP. N. Vosburgh
Dynergy CorporationP.O. BOX 4281269 Union AvenueLaconia, NH 03246Attn: R. B., Allen
General Manager
American Wind Energy Association1609 Connecticut Avenue NWWashington, DC 20009
South Dakota School of Minesand Technology
Department of Mechanical EngineeringRapid City, SD 57701Attn: E. E. Anderson
University of Vermont318 Minis HallBurlington, VT 05405Attn: S, Anderson
US DOE/Office of Commercialization20 Massachusetts Avenue NWMain Station 2221CWashington, DC 20585Attn: G. T. Ankrum
Stanford UniversityDepartment of Aeronautics and
Astronautics Mechanical EngineeringStanford, CA 94305Attn: H. Ashley
Consolidated Edison Company ofNew York, Inc.
4 Irving PlaceNew York, NY 10003Attn: K. Austin
Hayes, Seay, Mattern & Mattern1315 Franklin Road SWRoanoke, VA 24016Attn: B. H. Barksdale, Jr.
University of CaliforniaInstitute of Geophysics
and Planetary PhysicsRiverside, CA 92521Attn: P. J. Baum
Washington State UniversityDepartment of Electrical EngineeringCollege of EngineeringPullman, WA 99163Attn: F. K. Bechtel
Arizona State UniversitySolar Energy CollectionUniversity LibraryTempe, AZ 85281Attn: M. E. Beecher
Civilingenior, MCIF“Osterbyhus,” 6990 UlfborgDK6990 DENMARKAttn: L. Bjervig
University of OklahomaAero Engineering DepartmentNorman, OK 73069Attn: K. Bergey
Wind Energy SystemsRoute 1, Box 93-AOskaloosa, KS 66066Attn: S. Blake
112
Distribution: (Cent)
McDcmnell Douglas Aircraft CorporationDepartment 341, Building 32/2P.O. BOX 516St. Louis, MO 63166Attn: R. Brulle
University of SherbrookeFaculty of Applied ScienceSherbrooke, QuebecCANADA JIK 2R1Attn: R. Camerero
CERCEM (2)49 Rue du Commandant Rolland93350 Le BourgetFRAFJCEAttn: G. Darrieus
J. Delassus
University of AucklandSchool of EngineeringPrivate BagAuckland, NEW ZEALANDAttn: V. A. L. Chasteau
Professor
McDonnell Aircraft CorporationP.O. 130x 516Department 337, Building 32St. Lc,uis, MO 63166Attn: H. T. Clark
USDA, Agricultural Research ServiceSouthwest Great Plains Research
CenterBushland, TX 79012Attn: R. N. Clark
State Consumer Protection BoardState of New YorkExecutive Department99 Washington AvenueAlbarly, NY 12210Attn: J. D. Cohen
Consumer Outreach Coordinator
University of MassachusettsMechanical and Aerospace Engineering
DepartmentAmherst, MA 01003Attn: D. E. Cromack
Associate Professor
Tumac Industries650 Ford StreetColorado Springs, CO 80915Attn: G. B. Curtis
US Department of Energy/ALO (3)Albuquerque, NM 87185Attn: G. P. Tennyson
D. C. GravesD. W. King
US Department of Energy Hq (20)Washington, DC 20545Attn: L. V. Divone, Chief
Wind Systems BranchD. F. Ancona, Program Manager
Wind Systems BranchC. E. Aspliden
Southern Illinois UniversitySchool of EngineeringCarbondale, IL 62901Attn: C. W. Dodd
Kaiser Aluminum and Chemical Sales, Inc.6177 Sunol Blvd.
. P. O. BOX 877Pleasonton, CA 94566Attn: D. D. Doerr
Dominion Aluminum Fabricating Ltd. (2)3570 Hawkestone RoadMississauga, OntarioCANADA L5C 2U8Attn: L. Schienbein
C. Wood
Hamilton Standard1730 NASA BoulevardRoom 207Houston, TX 77058Attn: D. P. Dougan
Nederlands Energy Research Foundation(E. C.N.)
Physics DepartmentWesterduinweg 3 Patten (nh)THE NETHERLANDSAttn: J. B. Dragt
Battelle-Pacific Northwest LaboratoryP.O. Box 999Richland, WA 99352Attn: C. E. Elderkin
113
Distribution: (Cent)
The Mitre Corporation1820 Dolley Madison Blvd.McLean, VA 22102Attn: F. R. Eldridge, Jr.
Electric Power Research Institute3412 Hillview AvenuePalo Alto, CA 94304Attn: E. Demeo
The Resources AgencyDepartment of Water ResourcesEnergy Division1416 9th StreetP. O. BOX 388Sacramento, CA 95802Attn: Richard G. Ferreira, Chief
University of ColoradoDepartment of Aerospace Engineering
SciencesBoulder, CO 80309Attn: J. D. Fock, Jr.
New England GeosystemsP. O. BOX 128East Derry, NH 03041Attn: D. R. Finley
Public Service Company of New Hampshire1000 Elm StreetManchester, NH 03105Attn: L. C. Frederick
University Laval - QuebecMech. Eng. Dept.Faculty of Sciences & Eng.Quebec, CANADA GIK 7P4Attn: H. Gerardin
Amarillo CollegeAmarillo, TX 79100Attn: E. Gilmore
Wind Power DigestP.O. Box 539Harrisburg, PA 17108Attn: P. Gipe
University College of SwanseaDepartment of Mechanical EngineeringSingleton ParkSwansea SA2 8PPUNITED KINGDOMAttn: R. T. Griffiths
Massachusetts Institute of Technology77 Massachusetts AvenueCambridge, MA 02139Attn: N. D. Ham, Professor
Kaiser Aluminum and Chemical Sales, Inc.14200 Cottage Grove AvenueDolton, IL 60419Attn: A. A. Hagman
Project DepartmentElectricity Supply18 St. Stephen’s GreenDublin 2, IRELANDAttn: M. L. Hally, Section Manager
US Department of Energy/DST20 Massachusetts AvenueWashington, DC 20545Attn: S. Hansen
Wind Engineering CorporationAirport Industrial AreaBOX 5936Lubbock, TX 79415Attn: C. F. Harris
Massachusetts Institute of TechnologyAero /Astro DepartmentCambridge, MA 02139Attn: W. L. Harris
Rockwell International (2)Rocky Flats PlantP.O. BOX 464Golden, CO 80401Attn: T. Healy
HelionP.O. Box 4301Sylmar, CA 91342
114
Distribution: (Cent)AMBIOKVA
Fack, S-10405
StockholmSWEDEN
Attn: D. HinrichsenAssociate Editor
Sven HugossonBOX 21048S. 10031 Stockholm 21SWEDEN
Ben-Gurion University of the NegevDepartment of Mechanical EngineeringBeer-Sheva, ISRAELAttn: O. Igra
Indian Oil Corporation, Ltd.Marketing Division254-C, Dr. Annie Besant RoadPrabhadevi, Bombay-400025INDIA
JBF Scientific Corporation2 Jewel DriveWilmington, MA 01887Attn: E. E. Johanson
Kansas State UniversityElectrical Engineering DepartmentManhattan, KS 66506Attn: G. L. Johnson, P. E.
B. O. Kaddy, Jr.Box 35331 Union StreetHillsboro, NH 03244
Kaman Aerospace CorporationOld Windsor RoadBloomfield, CT 06002Attn: W. Batesol
R. L. Katzenberg2820 Upton St. NWWashington, DC 20008
The College of Trades and TechnologyP.O. ]Box 1693Prince Philip DriveSt. John’s, NewfoundlandCAN.ADA AIC 5P7Attn: R. E. Kelland
Natural Power, Inc.New Boston, NH 03070Attn: S. King
Larry KinnettP.O. BOX 6593Santa Barbara, CA 93111
Michigan State UniversityDivision of Engineering ResearchEast Lansing, MI 48824Attn: O. Krauss
Lawrence Livermore LaboratoryP.O. BOX 808 L-340Livermore, CA 94550Attn: D. W. Dorn
Public Service Company of New MexicoP.O. BOX 2267Albuquerque, NM 87103Attn: M. Lechner
Reynolds Metals CompanyMill Products Division6601 West Broad StreetRichmond, VA 23261Attn: G. E. Lennox
Industry Director
Kalman Nagy LehoczkyCort Adelers GT.300s10 2NORWAY
State Energy CommissionResearch and Development Division1111 Howe AvenueSacramento, CA 95825Attn: J. Lerner
Agriculture Research CenterUSDABuilding 303Beltsville, MD 20705Attn: L. Liljidahl
Aeroenvironment, Inc.660 South Arroyo ParkwayPasadena, CA 91105Attn: P. B. S. Lissaman
115
Distribution: (Cent)
Wehrtechnik und EnergieforschungERNO-Raumfahrttechnik GmbHHunefeldstr. 1-5Postfach 1059092800 Bremen 1GERMANYAttn: H. Seizer
Dipl.-Phys.
Bristol Aerospace Ltd.Rocket and Space DivisionP.O. BOX 874Winnipeg, ManitobaCANADA R3C 2S4Attn: H. Sevier
National Aeronautical LaboratoryAerodynamics DivisionBangalore 560017INDIAAttn: P. N. Shankar
Kingston PolytechnicCanbury Park RoadKingston, SurreyUNITED KINGDOMAttn: D. Sharpe
Cornell UniversitySibley School of Mechanical and
Aerospace EngineeringIthaca, NY 14853Attn: D. G. Shepherd
Colorado State University (2)Mechanical Engineering Department HeadFt. Collins, CO 80521Attn: H. P. Sleeper
F. Smith
Instituto Tecnologico Costa RicaApartado 159 CartagoCOSTA RICAAttn: K. Smith
Iowa State UniversityAgricultural Engineering, Room 213Ames, IA 50010Attn: L. H. Soderholm
Southwest Research Institute (2)P.O. Drawer 28501San Antonio, TX 78284Attn: W. L. Donaldson,
Senior Vice PresidentR. K. Swanson
Bent SorensonRoskilde University CenteryEnergy JGroup, Bldg. 17.2IMFUFAP. O. BOX 260DK-400 RoskildeDENMARK
Rick StevensonRoute 2BOX 85Springfield, MO 65802
Morey /Stjernholm and Associates1050 Magnolia StreetColorado Springs, CO 80907Attn: D. T. Stjernholm, P.E.
Mechanical Design Engineer
G. W. Stricker383 Van Gordon 30-559Lakewood, CO 80228
C. J. SwetRoute 4BOX 358Mt. Airy, MD 21771
National Research CouncilASEB2101 Constitution Ave.Washington, DC 20418Attn: J. Taylor
NRC-National Aeronautical (3)Establishment
Low Speed Aerodynamics SectionOttawa 7, OntarioCANADA KIA 0R6Attn: R. J. Templin
.
118
Distribution: (Cent)
Texas Tech University (3)P.O. Box 4389Lubbock, TX 79409Attn: K. C. Mehta
CE DepartmentJ. Strickland
ME DepartmentJ. Lawrence
ME Department
Atari, Inc.155 Mc~ffett Park DriveSunnyvale, CA 94086Attn: F. Thompson
Air Force Wright AeronauticalLaboratories (AFSC)
Terrestrial Energy TechnologyProgram Office
Aerospace Power DivisionAero Propulsion LaboratoryWright-Patterson Air Force Base,OH 45433Attn: J. M. Turner, Group Leader
United Engineers and Constructors, Inc.Advanced Engineering Department30 South 17th StreetPhiladelphia, PA 19101Attn: A. J. Karalis
University of New Mexico (2)New Mexico Engineering Research
InstituteCampus P.O. Box 25Albuquerque, NM 87131Attn: D. E. Calhoun
G. G. Leigh
University of New Mexico (2)Albuquerque, NM 87106Attn: K. T. Feldman
Energy Research CenterV. Sloglund
ME Department
Jan VacekEolienne experimentalC.P. 279, Cap-aux-MeulesIles de la Madeleine, QuebecCANADA
Solar Energy Research Institute1617 Cole Blvd.Golden, CO 80401Attn: I. E. Vas
National Aerospace LaboratoryAnthony Fokkerweg 2Amsterdam 1017THE NETHERLANDSAttn: O. de Vries
West Virginia UniversityDepartment of Aero Engineering1062 Kountz AvenueMorgantown, WV 26505Attn: R. Walters
Bonneville Power AdministrationP.O. BOX 3621Portland, OR 97225Attn: E. J. Warchol
Energy and Power SystemsERA Ltd.Cleeve Rd.LeatherheadSurrey KT22 7SAENGLANDAttn: D. F. Warne, Manager
G. R. Watson, Project ManagerThe Energy CenterPennine House4 Osborne TerraceNewcastle upon Tyne NE2 lNEUNITED KINGDOM
Watson Bowman Associates, Inc.1290 Niagara St.Buffalo, NY 14213Attn: R. J. Watson
Tulane UniversityDepartment of Mechanical EngineeringNew Orleans, LA 70018Attn: R. G. Watts
Solar Energy Research Institute (3)1617 Cole Blvd.Golden, CO 80401Attn: P. Weis
119
Distribution: (Cent)
Mississippi State UniversityMechanical Engineering DepartmentMississippi State, MS 39762Attn: W. G. Wells, P.E.
Associate Professor
University of AlaskaGeophysical InstituteFairbanks, AK 99701Attn: T. Wentink, Jr.
West Texas State UniversityGovernment Depository Library
Number 613Canyon, TX 79015
Wind Energy ReportBox 14102 S. Village Ave.Rockville Centre, NY 11571Attn: F. S. Seiler
Wind Program ManagerWisconsin Division of State Energy8th Floor101 South Webster StreetMadison, WI 53702
Central Solar Energy ResearchCorporation
1200 Sixth Street328 Executive PlazaDetroit, MI 48226Attn: R. E. Wong
Assistant Director
100012003161
31614533
470047104715471547154715
4715
47154715
471547154715
471555205523552355235600
5620
563056325633563356365636563656508214
G. A. FowlerL. D. SmithJ. E. Mitchell (15)P. S. WilsonJ. W. ReedJ. H. ScottG. E. BrandvoldR. H. Braasch (200)J. D. CyrusR. D. GroverE. G. KadlecP. C. Klimas (15)M, T. MattisonR. O. NellumsW. N. SullivanM. H. WorstellR. A. WatsonD. F. WolfT. B. LaneD. W. LobitzR. C. Reuter, Jr.T. G. CarrieD. B. SchusterM. M. NewsomR. C. MaydewC. W. PetersonS. McAlees, Jr.R. E. SheldahlJ. K. ColeD. E. BergW. H. CurryD. J. RigaliM. A. Pound
15)
3141 L. J. Erickson (5)3151 W. L. Garner (3)
For DOE/TIC (Unlimited Release)
120 *U.S. GOVERNMENT PRINTING OFFICE: 1981-0-777-023/567
