DAVID W. TAYLOR NAVAL SHIP SRESEARCH AND DEVELOPMENT CENTER · DAVID W. TAYLOR NAVAL SHIP SRESEARCH...
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CIng 0 DAVID W. TAYLOR NAVAL SHIP SRESEARCH AND DEVELOPMENT CENTER u.,Bethesda, Md. 20084 z ANALYSIS OF WAKE SURVEY AND BOUNDARY LAYER MEASUREMENTS z < FOR THE R/V ATHENA REPRESENTED BY MODEL 5366 IN THE ANECHOIC WIND TUNNEL 00 BY RAE B. HURWITZ . ,AND DTIC O DOUGLAS S. JENKINS ELECTE C JUL23 1980 B APPROVED FOR PUBLIC RELEASE: DISTRIBUTION UNLIMITED z w z %D SHIP PERFORMANCE DEPARTMENT REPORT Li...JULY 1980 DTNSRDC/SPD-0833- 02 807 21026
Transcript of DAVID W. TAYLOR NAVAL SHIP SRESEARCH AND DEVELOPMENT CENTER · DAVID W. TAYLOR NAVAL SHIP SRESEARCH...
CIng
0
DAVID W. TAYLOR NAVAL SHIPSRESEARCH AND DEVELOPMENT CENTER
u.,Bethesda, Md. 20084
z
ANALYSIS OF WAKE SURVEY AND BOUNDARY LAYER MEASUREMENTSz< FOR THE R/V ATHENA REPRESENTED BY MODEL 5366 IN
THE ANECHOIC WIND TUNNEL
00 BY
RAE B. HURWITZ.,AND DTICO DOUGLAS S. JENKINS ELECTE
C JUL23 1980B
APPROVED FOR PUBLIC RELEASE: DISTRIBUTION UNLIMITED
z w
z
%D SHIP PERFORMANCE DEPARTMENT REPORT
Li...JULY 1980 DTNSRDC/SPD-0833- 02
807 21026
MAJOR DTNSRDC ORGANIZATIONAL COMPONENTS
DTNSRDC
COMMANDER 00
I TECHNICAL DIRECTOR01
OFFICER-IN-CHARGE OFFICER-IN-CHARGECARDEROCK ANNAPOLIS05 04,
SYSTEMSDEVELOPMENTDEPARTMENT
SHIP PERFORMANCE AVIATION ANDDEPARTMENT SURFACE EFFECTS
15 DEPARTMENT
STRUCTURES COMPUTATION,DEPARTMENT MATHEMATICS ANDDEATETILOGISTICS DEPARTMENT
17 18
SHIP AC C PROPULSION AND•SHIP ACOUSTICS ____-_
DEPARTMENT AUXILIARY SYSTEMS19 DEPARTMENT
19 27
SHIP MATERIALS CENTRALENGINEERING INSTRUMENTATION
, DEPARTMENT 28 DEPARTMENTri,
$ __ ___ ___ ____ ___ ___ ____ ___ ___ f q
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+0DNSRDC/SD 3-2j0
AALYSIS OF *KE SURVEY AND UNDARYIYERrZSUREMENTdSIORNE RE A'1Ii 0D(9 FNLD
WODEL 5366 IN THE AN CHOI WI UNNE- 7-IJ 6*-.~-. ~ ~ .~ . CONTRACT OR GRANT NUMBER(&)
.)REB./HUWiT -M DOUGLAS S S--^-
3. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT. PROJECT. TASKAREA 6 WORK UNIT NUMBaERS
DAVID W. TAYLOR NAVAL SHIP R&D CENTER Program Element 63508NSHIP PERFORMANCE DEPARTMENT Task Area S0379001 Tank 19977BETHESDA. MARYLAND 20084 -Work Unit 1524-641
1I. CONTROLLING OFFICE NAME AND ADDRESS 12. REPORT DATE
NAVAL SEA SYSTEMS COMMAND (NAVSEA 05R) JULY 1980WASHINGTON, D. C. 20362 13. NUMBER OF PAGES
7R + wil14. MON'T(ID 'J Ar' Cv "4m N~I .~4 SI different from Controlling Office) 15. SECURITY CLASS. (of this report)
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WAKE SURVEYBOUNDARY LAYERWIND TUNNELMODEL EXPERIMENTS
20 ABSTRACT (Continue on rvers* de If necesary ad Identify by block nlumlber) The results of wake survey
and boundary layer profile measurements-sre-presented ,o oe rpeetna twin-screw displacement ship. These measurements were obtained in a windtunnel using hot wire anemometers. Wake surveys were conducted in the propelleidisk and ahead of the propeller plane with and without the propeller operating.Circumferential distribuLions of the longitudinal, tangentlal, and radial veloc tycomponents at four radial locations and a harmonic anal.ysis of each componentare included. The boundary layer profile measurements were obtained at three
DDI',~, 1473 EDITION OF I NOV 65 s oSsoL. rE Unclassified
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i SECURITY CLASSIFICATION Of THIS PACE ("hen Dela EnAtrd)Ilj
UNCLASSIFIED
SECURT CLASSIFICATION OF TIS PAGE (When ate eet)
20.,,longitudinal locations in the area of the shafting and struts. A comparisonof full-scale, model-scale towing tank, and wind tunnel measurements ispresented. Model-scale boundary layer velocity profiles ahead and astern ofthe propeller plane were smaller than the full-scale profiles. The model wakesurveys ahead of the propeller plane showed no significant differences withand without the propeller operating. The data from the wind tunnel wake surveyin the propeller plane agreed better with the full-scale data than the towingtank data.
I -l
ii UNCLASSIFIED
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ZVI,
TABLE OF CONTENTS
page1
LIST OF' FIGURES iv
LIST OF TABLES Viii
NOTATION ix
ABSTRACT 1
ADNINISTRATIVE INFORM4ATION 1
INTRODUCTION 1
DESCRIPTION OF EXPERIMENTS 3
DESCRIPTION OF EXERIMENTAL APPARATUS 4
PRESEN~TATION AND DISCUSSION OF RESULTS
Boundary Laye r Experiments 7Tr ansverse Wake Survey Expeiriments 9R.tational Wake Survey Experiment 12
Scrut Wake Excperimient 14
CON CLUS IONS 15
REFEREN4CES 17
APPJENDT-X A -VELOCITY COMPONENT RATIOS AND HARMONIC ANALYSIS OF THE '46TRANSVERSE WAKE SURVEY EXPERIMENTS WITH AND WITHOUTAN OPERATING PROPELLER
~ P~NI~ -VELOCITY COMPONENT RATIOS AND HARMONIC ANALYSIS OF THE 65VROTATIONAL WAKE SURVEY EXPERIMENT
ACCESSION for
flEESWhite SectionDuhBuff Section 0
UNANNOUNCED 13IuSTICATION - -
BY
S -S
-a'or E Qv.
LIST OF FIGURES Page
1- Ship and Model Data for R/V ATHENA Represented by Models 5365 and5366 18
2 - Controllable Pitch Propeller Geometry- Propellers 4710, 4711, and4712 19
3 - Plan View of Hull Showing Boundary Layer Rake Locations 20
4 - - Longitudnal Locations of Wake Survey and Strut WakeMeasurements on Model 5366 21
b - Transverse Grid Locations of Measurements of Experiments2 and 3 21
5 - Afterbody Sections of R/V ATHENA Showing Radii of Wake Measurements 22
6 - Double Model Installed in DTNSRDC Wind Tunnel for Boundary Layer
and Rotational Wake Survey Experiments 23
7 Double Model Installed in DTNSRDC Wind Tunnel for Transverse WakeSurvey Experiments 23
8 Experimental Set-up for Boundary Layer Experiments 24
9 Close-up View of Boundary Layer Rake Locations 24
10 Close-up View of Boundary Layer Probe with Operating Propeller 25
11 -Single-Sensor Hot Wire Anemometer Probe Used for Boundary LayerProfile Measurements 25
12 -Experimental Set-up for Transverse Wake Survey and Strut WakeMeasurements 25
13 - Triple-Sensor Hot Wire Anemometer Probe Used for Wake SurveyMeasurements 26
14 - Hot Wire Probe Mounted with Drive Motor for Rotational WakeSurvey Experiment 26
15 -Measured Boundary Layer Velocity Profiles for R/V ATHENA and WindTunnel Model 5366 with and without Propeller at Locations 1 and 8 27
16 - Measured Boundary Layer Velocity Profiles for R/V ATHENA and WindTunnel Model 5366 with and without Propeller at Locations 2 and 6 28
17 - Measured Boundary Layer Velocity Profiles for R/V ATHENA and WilidTunnel Model 5366 with and without Propeller at Locations 3 and 7 29
iv
LIST OF FIGURES (continuedPage
18 - Velocity Component Ratios for R/V ATHENA and Model 5366 atthe Forward Rake Location (X/LwL - 0.906) with an OperatingPropeller for the 0.417 Radius 30
19 Velocity Component Ratios for R/V ATHENA and Model 5366 atthe Forward Rake Location (x/LwL - 0.906) with an OperatingPropeller for the 0.583 Radius 31
20 - Velocity Component Ratios for R/V ATHENA and Model 5366 atthe Forward Rake Location (X/LwL = 0.906) with an OperatingPropeller for the 0.750 Radius 32
21 - Velocity Component Ratios for R/V ATHENA and Model 5366 atthe Forward Rake Location (X/LWL = 0.903 with an OperatingPropeller for the 0.917 Radius 33
22 - Velocity Component Ratios for R/V ATHENA and Model 5366 atthe Forward Rake Location (X/LwL = 0.906) with an OperatingPropeller for the 1.083 Radius 34
23 - Velocity Component Ratios for R/V ATHENA and Model 5366 atthe Forward Rake Location (X/LWL - 0.906) without an OperatingPropeller for the 0.417 Radit.: 35
24 - Velocity Component Ratios for R/V ATHENA and Model 5366 atthe Forward Rake Location (X/LwL = 0.906) without an OperatingPropeller for the 0.583 Radius 36
25 - Velocity Component Ratios for R/V ATHENA and Model 5366 atthe Forward Rake Location (X/LwL - 0.906) without an OperatingPropeller for the 0.750 Radius 37
-26 - Velocity Component Ratios for P,/V ATHENA and Model 5366 at
the Forward Rake Location (x/LwL = 0.906) without an OperatingPropeller for the 0.917 Radius 38
27 - Velocity Component Ratios for R/V ATHENA and Mo..el 5366 atthe Forward Rake Location (x/LwL = 0.906) without an OperatingPropeller for the 1.083 Radius 39
28 - Composite Plot of Velocity Component Ratios for R/V ATHENA andModels 5365 and 5366 at the Propeller Rake Location (x/LWL 0.949)for the 0.456 Radius 40
29 - Composite Plot of Velocity Component Ratios for R/V ATHENA andModels 5365 and 5366 at the Propeller Rake Location (X/LwL 0.949)for the 0.633 Radius 41
V
cI
- ..
LIST OF FIGURES (continued)Page
30 - Composite Plot of Velocity Component Ratios for R/V ATHENA andModels 5365 and 5366 at the Propeller Rake Location(X/LwL = 0.949) for the 0.781 Radius 42
31 - Composite Plot of Velocity Component Ratios for R/V ATHENA andModels 5365 and 5366 at the Propeller Rake Location(x/LwL = 0.949) for the 0.963 Radius 43
32 - Strut Wake Measurements at the Location X/LwL - 0.938 44APPENDICES
A-1 - Composite Plot of Velocity Ccmponent Ratios from the TransverseWake Surveys at the Forward Rake Location for the InterpolatedRadius of 0.456 47
A-2 - Composite Plot of Velocity Component Ratios from the TransverseWake Surveys at the Forward Rake Location for the InterpolatedRadius of 0.633 48
A-3 - Composite Plot of Velocity Component Ratios from the TransverseWake Surveys at the Forward Rake Location for the InterpolatedRadius of 0.781 49
A-4 - Composite Plot of Velocity Component Ratios from the TransverseWake Surveys at the Forward Rake Location for the InterpolatedRadius of 0.963 50
A-5 - Radial Distribution of the Mean Velocity Component Ratios fromthe Transverse Wake Survey at the Forward Rake Location withan Operating Propeller 51
A-6 - Radial Distribution of the Mean Advance Angle and Advance AngleVariations from the Transverse Wake Survey at the Forward RakeLocation with an Operating Propeller 52
A-7 - Radial Distribution of the Mean Velocity Component Ratios fromthe Transverse Wake Survey at the Forward Rake Locationwithout an Operating Propeller 53
A-8 - Radial Distribution of the Mean Advance Angle and Advance AngleVariations from the Transverse Wake Survey at the Forward RakeLocation without an Operating Propeller 54
B-1 - Velocity Component Ratios for Model 5366 from the RotationalWake Survey at the Propeller Rake Location for the 0.456 Radius 66
B-2 - Velocity Component Ratios for Model 5366 from the Rotational
Wake Survey at the Propeller Rake Location for the 0.633 Radius 67
vi
LIST OF FIGURES (continued)Page
B-3 - Velocity Component Ratios for Model 5366 from the RotationalWake Survey at the Propeller Rake Location for the 0.781 Radius 68
B-4 - Velocity Component Ratios for Model 5366 from the RotationalWake Survey at the Propeller Rake Location for the 0.963 Radius 69
B-5 - Radial Distribution of the Mean Velocity Component Ratios from
the Rotational Wake Survey at the Propeller Rake Location 70
B-6 - Radial Distribution of the Mean Advance Angle and Advance 14
Angle Variations from the Rotational Wake Survey at thePropeller Rake Location 71
F.vii
LI
vii
LIST OF TABLESPage
1 Experimental Program 45
A-i - Listing of the Mean Velocity Component Ratios, the Mean AdvanceAngles and other Derived Quantities at the Experimental andInterpolated Radii of the Transverse Wake Survey with an OperatingPropeller 55
A-2 - Harmonic Analyses of Longitudinal Velocity Component Ratios at theExperimental and Interpolated Radii of the Transberse Wake Surveywith an Operating Propeller 56
A-3 - Harmonic Analyses of Tangential Velocity Component Ratios at theExperimental and Interpolated Radii of the Transverse Wake Surveywith an Operating Propeller 58
A-4 - Listing of the Mean Velocity Component Ratios, the Mean AdvanceAngles and other Derived Quantities at the Experimental and theInterpolated Radii of the Transverse Wake Survey without anOperating Propeller 60
A-5 - Harmonic Analyses of Longitudinal Velocity Component Ratios at theExperimental and Interpolated Radii of the Transverse Wake Surveywithout an Operating Propeller 61
A-6 - Harmonic Analyses of Tangential Velocity Component Ratios at theExperimental and Interpolated Radii of the Transverse Wake Surveywithout an Operating Propeller 63
B-1 - Listing of the Mean Velocity Component Ratios, the Mean AdvanceAngles and other Derived Quantities at the Experimental andInterpolated Radii of the Rotational Wake Survey 72
B-2 - Harmonic Analyses of Longitudinal Velocity Component Ratios at ther - Experimental Radii of the Rotational Wake Survey 73
B-3 - Harmonic Analyses of Longitudinal Velocity Component Ratios at theInterpolated Radii of the Rotational Wake Survey 74
B-4 - Harmonic Analyses of Tangential Velocity Component Ratios at theExperimental Radii of the Rotational Wake Survey 76
B-5 - Harmonic Analyses of Tangential Velocity Component Ratios at theInterpolated Radii of the Rotational Wake Survey 77
viii
• ('s- -
,-":1 ; | ' t°
" ' -- ' ' - k
NOTATION
CONVENTIONAL SYMBOL APPEARINGSYMBOL ON PLOTS DEFINITION
AN COS COEF The cosine coefficient of theNth harmonic*
BN SIN COEF The sine coefficient of theNt harmonic*
D Propeller diameter
JV Apparent advance coefficientJ i V (dimensionless)
nDLWL Waterline length
N N Harmonic number
n Propeller revolutions
Rn Reynolds number based on length
r/R or x Radius or RAD. Distance (r) from the propelleraxis expressed as a ratio of thepropeller radius (R)
V V Actual model or ship velocity
Vb(X,0) Resultant inflow velocity toblade for a given point
V (x) Mean resultant inflow velocityto blade for 3 given radius
V (x,6 ) VR Radial component of the fluidr. velocity for a given point
(positive toward the shaft~~centerl ine)"
" r(X) Mean radial velocity component
for a given radius
V (x,8)/V VR/V Radial velocity component ratLo; rr for a given point
Vr(X)/V VRBAR Mean radial velocity componentr ratio for a given radius
V VT Tangential component of thet fluid velocity for a given point
(positive in a counterclockwisedirection looking forward)
j*See footnote on the following page
**See footnote on the following page
F"x
NOTATION (Continued)
V (x) Mean tangential velocity componentfor a given radius
V (x, 8)/V VT/V Tangential velocity componentratio for a given point
V t x)/V VTBAR Mean tangential velocity componentratio for a given radius
(V W/V) AMPLITUDE Amplitude (B for single screwsymmetric; CN otherwise) of Nth
harmonic of the tangential velocitycomponent ratio for a given radius*
Vx(X,O) VX Longitudinal (normal to the plane
of survey) component of the fluidvelocity for a given point (positivein the astern direction)
V x) Mean longitudinal velocity com-ponent for a given radius
Vx (x,e)/V VX/V Longitudinal velocity componentratio for a given point
V (x)/V VXBAR Mean longitudinal velocity componentratio for a given radius
(Vx (X)/V) N AMPLITUDE Amplitude (AN for single screw
symmetric; CN otherwise) of Nth
harmonic of the longitudinalvelocity component ratio for a "
given radius*
X/LwL Longitudinal position aft offorward perpendicular
"N PHASE ANGLE Phase angle of Nth harmonic*
The harmonic amplitudes of any circumferential velocity distribution f (8)are the coefficients of the Fourier Series:
II
f() = A0 +I AN cos (NG) +Y BN sin(NO)
A0 + CN sin(NO + 0N)
To avoid confusion it should be noted that subscript x refers to
longitudinal component, whereas x as a parameter is used to define adistance (radial or longitudinal).
x
NOTATION (Continued)
l-w(x) l-WX Volumetric mean velocity ratiofrom the hub to a given radius
r/R
j 2 (V x)/V) x dx
1-w(r/R)
rhb/R
(r/R) (rb/R)2
and V (x,6)/V =(V (X,9)/V)
-(V t(x,e)/V) tan (0(x,8))I
1-wv<IK) l-WVX Volumetric mean velocity ratio fromthe hub to a given radius (without the
tangential velocity correction)
rIR
k2 (V()V x dx
L-w(r/R) = rh /R
2 2
~(xO --- Advance angle in degrees for a givenpoint
OWx BBAR Mean advance angle in degrees for agiven radius
+A, BPOS Variation of the maximuim advance aagleIfrom the mean for a given radius
xi
NOTATION (Continued)
BNEG Variation of the minimum advanceangle from the mean for a givenradius
Angle in Degrees Position angle (angular coordinate)in degrees
Kinematic viscosity of fluid medium
.0114 Plane of
7rx/J V- __V__ _ Propeller
VELOCITY DIAGRAM OF BETA ANGLES
ENGLISH/SI EQUIVALENTS
ENGLISH SI
1 inch 25.400 millimeter [0.0254 m ( meter))
1 foot 0.3048 m (meter)
1 foot per second 0.3048 m/s (meter per second)
1 knot 0.5144 m/s (meter per second)
1 pound (force) 4.4480 N (Newtons)
1 degree (angle) 0.01745 tad (radians)
1 horsepower 0.7457 kW (kilowatts)
1 long ton 1.016 tonnes, 1.016 metric tons, or 1016 kilograms
1 inch Water (60 F) 248.8 pa (pascals) ]xii
ABSTRACTThe results of wake survey and boundary layer profile
measurements are presented for a model representing a twin-screw displacement ship. These measurements were obtainedin a wind tunnel using hot wire anemometers. Wake surveyswere conducted in the propeller disk and ahead of thepropeller plane with and without the propeller operating.
Circumferential distributions of the longitudinal, tangential,and radial velocity components at four radial locations anda harmonic analysis of each component are included. Theboundary layer profile measurements were obtained at threelongitudinal locations in the area of the shafting end struts.A comparison of full-scale, model-scale towing tank, andwind tunnel measurements is presented. Model-scale boundarylayer velocity profiles ahead and astern of the propellerplane were smaller than the full-scale profiles. The model
wake surveys ahead of the propeller plane showed no signi-ficant differences with and without the propeller operating.The data from the wind tunnel wake survey in the propellerplane agreed better with the full-scale data than the
towing tank data.
ADMINISTRATIVE INFORMATION
Model experiments were performed under the Controllable Pitch Propeller
Research Program sponsored by the Naval Sea Systems Command (NAVSEA 05R)
and administered by the David W. Taylor Naval Ship R&D Center (DTNSRDC).
The project was funded under DTNSRDC Task Area S0379001 and Work Unit
1-1524-641.
INTRODUCTION
As part of the Controllable Pitch Propeller Research Program, the
DTNSRDC conducted full-scale wake and boundary layer velocity profile
measurements on the high speed transom stern ship, R/V ATHENA. Project goals
were to obtain propeller disk velocity component ratios in the wake of a
[full-scale ship and to determine the effects of propeller induction on thedevelopment of the boundary layer. The full-scale wake measurements con-
sisted of the longitudinal, tangentialand radial velocity component ratios
ahead of and in the propeller plane. The full-scale boundary layer profile
'%,5
was obtained at three longitudinal locations in the area of the shafts and
struts with and without the propeller operating.
A series of model experiments was instituted to identify the differ-
ences between model- and full-scale wake data which would affect the operation
of controllable-reversible pitch propellers. Model-scale boundary layer
measurements were made to estimate the effects of the hull on the wake
distribution.
In an effort to correlate the results of the full-scale measurements,
experiments were conducted in the towing tank and wind tunnel at DTNSRDC.
Wake survey experiments in the plane of the propeller were conducted in
the towing tank with a i-to-8.25 scale model using five-hole spherical head
pitot tubes. Model-scale boundary layer profile measurements and wake
surveys in and ahead of the propeller plane were conducted in the Anechoic
Flow Facility (AFF) with a l-to-8.25 scale double model. The double model
was constructed so that the effect of the dynamic trim of the ship at 15
knots on the wake could be represented. Although the double model does not
allow the effects of the free surface to be accounted for, it does account
for the angle of the shafting, including the effects of dynamic trim, to
the undisturbed flow. The angle of the shafting to the free stream contrib-,
utes significantly to the tangential and radial velocity components.
The results of the wake surveys and boundary layer measurements obtained
on the double model are reported herein. Full-scale and towing tank data
are presented as comparisons with the wind tunnel wake survey and boundary
layer measurements. Harmonic analyses of the circumferential distributions
of the velocity component ratios obtained from the wind tunnel wake surveys
were performed and are reported herein. The results of the towing tank wake
surveys will be presented in a separate report.
2
40.
, ~26
DESCRIPTION OF EXPERIMENTS
The experimental program reported herein consisted of model-scale
'boundary layer and wake survey experiments in the Anechoic Flow Facility. The
Anechoic Flow Facility enabled measurements to be obtained at model-scale
Reynolds numbers with and without the propeller operating. A description
and aerodynamic calibration of the Anechoic Flow Facility is given by
1 2Brownell and Bowers 2
Five experiments were performed on a double model in the Anechoic Flow
Facility using hot wire anemometers. Table 1 summarizes the experimental
program. Experiment 1 consisted of boundary layer profile measurements
at six locations on the model corresponding to the locations of the full-
scale boundary layer measurements on the R/V ATHENA. Experiments 2 and 3
consisted of velocity measurements of the flow ahead of the propeller
plane with and without the propeller operating. These two experiments
were designed to measure the effect of the operating propeller on the flow
ahead of the propeller disk. Measurements were obtained at the same non-
dimensional axial location as those from the full-scale wake survey at
the forward rake location,x/LwL = 0.906. Experiments 2 and 3 are referred
to as the transverse wake surveys. Data were collected in a rectangular
grid perpendicular to the waterplane of the model. The hot wire probe
was moved in a horizontal direction at various vertical distances above
and below the propeller shaft centerline. The results from Experiments
1, 2, and 3 were correlated with the data from the full-scale wake
survey.
:References are listed on page 17
K'
Experiment 4 consisted of measurements cf the velocity defect in the
propeller plane due to the main vee struts. These measurements were obtained
in a rectangular grid perpendicular to the waterplane of the model.
The "rotational" wake survey, Experiment 5, was performed in the
propeller plane by rotating the hot wire anemometer to various circumfer-
ential positions at four radii from the shaft centerline. The radii at which
the measurements were made corresponded exactly to the full-scale and towing
tank wake survey radii, allowing a direct one-to-one compaiison of the data.
These radii were expressed as ratios of the local radius to the propeller
radius (r/R). A motor-driven unit which positions the hot wire anemometer
at discrete circumferential positions for a particular radial setting was
mounted behind the model, with its axis of rotation in line with the
propeller shaft.
DESCRIPTION OF EXPERIMENTAL APPARATUS A
The wind tunnel experiments were conducted with Model 5366 and Propeller
4712. Model 5366 is a double model of the twin-screw displacement ship,
R/V ATHENA. The double model was constructed of fiberglass to a linear
ratio of 8.25 with identical top and bottom hulls. The two halves were
joined together at a trimmed waterline corresponding to a ship speed of
15 knots. The model was appended with roll fins, shafting, struts, and a
V centerline skeg. Figure 1 shows model- and full-scale principal dimensions
for the R/V ATHENA.
Propeller 4712, a geosim of the R/V ATHENA design propellers, had a
[ ' stainless steel hub and fiberglass blades. Although the R/V ATHENA was
fitted with controllable-reversible pitch propellers, the blades of
Propeller 4712 were set at the design pitch. The propeller, propeller
4
shafting, and its bearings were designed to operate at a rotational rate
of 20,000 revolutions per minute and a wind tunnel speed of 61 meters per
second. The design of Propeller 4712 is shown in Figure 2 along with
Propellers 4710 and 4711 which were used in the towing tank experiments.
Commercially available one-component and three-component hot wire
anemometer probes were used to obtain all of the flow measurements in the
wind tunnel. Th: one-component probes measured the boundary layer profiles
(Experiment 1), and the three-component probes obtained the wake measure-
ments (Experiments 2 through 5). The one-component probe had a single-
sensor wire 1.25 mm in length and 5 pm in diameter held perpendicular to
the free stream velocity. The three-component probe had 3 mutually per-
pendicular wire sensors located within a 3 mm diameter sphere. Each wire
sensor was 1.25 mm in length and 5 pm in diameter at an angle of 54.7
degrees to the free stream.
Hot wire probes were probably the best measuring device to use because
of their small size and fast response time. Compared to spherical head Ipitot tubes normally used for wake surveys at DTNSRDC, hot wire probes
were more than three times smaller in diameter. The smaller size offered
less interference to the local flow. The fast responsp time allowed a
larger quantity of data samples. The pitot tube has a slower response
time and smaller sampling rate, and rapid fluctuations in the velocity are
not discernable. In addition, the size of the spherical head does not
allow the measurement of high velocity gradients which can be measured
by the smaller hot wire probes.
The small size of the hot wire probes makes them very susceptable
to breakage caused by particles in the fluid medium or by physical mis-
4
-"| - - S -
5
handling. In addition, output voltages are very sensitive to free stream
air temperature changes greater than 2.7 degrees Centigrade. Before Ind
after free stream calibrations and constant temperature monitoring were
required during each experiment due to this sensitivity. Free stream
calibrations were performed at least every three hours. Temperature
corrections were applied Lo the output voltages of the sensors based on
these calibrations.
The physical size of the hot wire probe enabled the measurements of
boundary layer velocity profiles and the wake ahead of an operating propeller.
Scragg and Sandell3 have shown that hot wire anemometers are at least as
accurate as five-hole pitot tubes. The boundary layer measurements were
repeatable within + 2 percentage points of the free stream velocity. The
wake m 3surements ahead of and in the propeller plane varied within + 2-to-5
percentage points for the longitudinal velocity component ratio, (V (x,9)/V).x
For wake surveys conducted in the deep water basin at DTNSRDC, the longitudinal
velocity component ratios are repeatable within + 1 percent, except in areas
4Vof high velocity gradients. In these areas, such as behind the shaft
struts or at the innermost radii, the five-hole pitot tube has much lower
accuracy. In the areas of high velocity gradients, hot wire probes may be
an order of magnitude more accurate than the five-hole pitot tubes.
Figure 3 shows the locations where measurements were taken to determine
velocities in the boundary layer of the R/V ATHENA and Model 5366. Trans-
ve:se wake survey and strut wake measurements were taken at the locations
presented in Figure 4. The nondimensional radii at which the measure-ents
were made for the rotational wake surveys are shown in Figure 5 and listed
in Table 1.
6
q4' f.
The model was mounted on its side for the boundary layer and rotational
wake survey experiments as shown in Figure 6. Figure 7 shows the double
model mounted in the horizontal waterplane configuration which was used for
the transverse wake surveys and the strut wake measurements.
The boundary layer profile measurements were obtained using a single-
sensor hot wire probe. This probe was moved in a horizontal direction by
a remotely controlled rack and pinion drive system. This system included
a stepping motor having a resolution of 0.02 nmm, and was mounted on a
vertical strut location in the free stream. The stepping motor was encased
in a streamlined piece of aluminum to reduce flow interference. A support
arm was attached to the vertical strut and the lower (starboard) shaft tube
in order to minimize the relative motion between the double model and the
vertical strut. Figures 8 through 10 show the experimental arrangement
designed for these experiments. The single-sensor is shown in Figure 11
with a scale in .he background.
Two sets of experiments, Experiments 2, 3, and 5, were performed using
triple-sensor hot wire probes shown in Figures 12 and 13. The transverse
wake survey consisted of measurements of the wake ahead of the propeller
plane with and without the propeller operating. Also, measurements of the
wake behind the struts were made. Figure 12 presents the experimental set-up
for these transverse measurements. The rotational wake survey was conducted
in the propeller disk at four radial locations using the motor-drive unit
mentioned previously. This motor had a variable rotational speed and an
internal triggering system. Measurements were obtained at 128 circumferential
locations. Figure 14 shows the experimental set-up for the rotational
wake survey. A7
-T
PRESENTATION AND DISCUSSION OF RESULTS
BOUNDARY LAYER EXPERIMENTS
The boundary layer profile measurements on Model 5366 were obtained
at a Reynolds number of 1.68 x 107, based on waterline length, in the wind
tunnel at Gix of the eight locations noted in Figure 3. Measurements, with
and without tne propeller operating, were obtained to study the effects of
propeller action on the boundary layer. Measurements were made at Locations
1, 2 and 3 without an operating propeller, and at Locations 8, 6, and 7 with
the propeller operating. No measurements were taken at Locations 4 and 5
because of the expected similarity with the velocity profiles at Locations
3 and 7, respectively. The full-scale boundary layer measurements, which
are presented in this report, were measured at a speed which corresponds
to a Reynolds number of 4.10 x 108.
Model-scale bou-4ary layer profiles with and without the propeller
operating, are plotted against the full-scale data at the corresponding
locations In Figures 15, 16, and 17. These data show the effect of the
propeller on the velocity profiles for both scales. The results at Locations
l and 8 showed a small increase in the velocity profile due to the propeller
for both model- and ship-scale. However, at Locations 3 and 7, behind the
propeller plane, the velocity defect in the boundary layer was greater
due to the operating propeller for both model and ship. For measurements
at Locations 2 and 6 for the wind tunnel model, there was no noticeable
difference in the data with or without the propeller operating. There
were no full-scale measurements at Location 6, shown in Figure 16, due
to the failure of that boundary layer probe. A comparison of the boundary
layer velocity profiles presented in these figures showed that the model-
scale profile is not as fully developed as the full-scale profile at
8
Locations 1 and 3. This was clearly a consequence of the one decade differ-
ence in Reynolds number between model aid ship. However, at Location 2,
the model- and full-scale profiles were quite similar. Neither profile
reached the free stream velocity within the expected range. Further analysis
indicated that there were no obvious errors in the collection of the model
data. Additional velocity profile measurements were conducted on the model
at several positions near Location 2. No unusual flow characteristics were
observed and there is still no explanation for this anomaly. The possibility
still exists for the full-scale measurements to be in error.
TRANSVERSE WAKE SURVEY EXPERIMENTS
Two wake surveys were conducted to measure the magnitude and direction
of the flow forward of the propeller disk. Experiment 2 was performed with
the propeller operating and Experiment 3 was conducted without the propeller
operating. Measurements were taken at 1.11 propeller diameters forward of the
propeller plane, x/LwL = 0.906, corresponding to the forward rake location
on the R/V ATHENA. Both experiments were performed in the wind tunnel at 38.1 m/s
corresponding to a Reynolds number of 1.40 x 1 Measurements were taken at
six equally spaced heights of 25.4 millimeters above and below the shaft centerline.
The vertical strut, shown in Figure 12, positioned the hot wire probe
enabling measurements to be taken at increments of 18 millimeters.
Velocity component ratios from conventional wake surveys done in the
towing tank at DTNSRDC are obtained radially and circumferentially in the
propeller plane. The wind tunnel data from Experiments 2 and 3 were
obtained in a rectangular grid perpendicular to the free stream velocity of
the wind tunnel. Computer programs were developed to present the data in
a cylindrical coordinate system, which is the coordinate system used in
94,
VI.
77'1
conventional wake surveys as described by Hadler and Cheng.5 The
longitudinal axis of this system was parallel to the propeller shaft center-
line. Once transformed, the data were interpolated to the nondimensionalI
It radii corresponding to the full-scale radii at the forward rake location,
x/LwL= 0.906. The radius ratios of these measurements were 0.417, 0.583,
0.750, 0.917 and 1.083 as listed in Table 1.
The results of the wake survey measurements on the R/V ATHENA and Model
5366 with an operating propeller (Experiment 2) are presented in Figures 18
through 22. The model-scale longitudinal velocity component ratios were
three to eight percent lower than the full-scale values. At the two inner
radii, 0.417 and 0.583, the full-scalp tangential and radial velocity
component ratios were slightly lower than the model-scale data between
0 and 180 degrees. There was good agreement with the radial velocity
component ratios at the two outer radii, 0.917 and 1.083 from 0 to 180
degrees.
Full-scale data taken on the starboard side as reported by Reed and
Day6 are presented in Figurec 23 through 27 along with the model data
from Experiment 3. These measurements were obtained forward of the
propeller plane without an operating propeller. The full-scale longitudinal
velocity component ratios were five-to-ten percent higher than the model-
scale. A large degree of scatter was observed in the full-scale
longitudinal velocity component ratios. The full-scale tangential
velo.ity component ratios were higher than those for Model 5366 between
the angles of 180 and 360 degrees. The full-scale radial velocity
component ratios were lower than the model-scale values.
10
Thr
4-. -.-. ~ ~ - '. ~- - - -
The wake survey data from Experiments 2 and 3 are presented in
Appendix A for all radii. Figures showing the effect of the propeller
suction on each of the three velocity component ratios for each radius at
model-scale, i.e., with and without a propeller turning, are also included
in Appendix A.
A harmonic analysis of the circumferential distribution of the
longitudinal and tangential velocities was performed. A diagram showing
the relationship between the longitudinal and tangential velocity vectors,
the advance coefficients and the advance angles is presented on page xii.
The mean longitudinal (V (x)/V), tangential (V (x)/V), and radial (V (x)/V)x t r
velocity component ratios, and volumetric mean wake velocity
ratio (1-w(x)) are presented in Appendix A for Experiments 2 and 3. These
quantities, except for the radial velocity component ratio,
are shown graphically in this appendix. The calculated mean values of the
advance angle (a(x)), and the maximum variations thereof, (+Aa) and (-A)
are given graphically and in tabular form in Appendix A. The advance
angles were calculated using an advance coefficient, J., of 0.739. The jF harmonic analyses of the circumferential distribution of the longitudinal
and tangential velocity component ratios at the experimental and interpolated
radii are presented in Appendix A for Experiments 2 and 3.
Wake survey measurements were made on the port side of the double
model for Experiments 2 and 3. No significant differences of the velocity
component ratios of these two experiments were observed. The small
variations shown in Figures A-i through A-8 were due to the limitations
of the numerical interpolation. No model data was available from 260 to 360
degrees because the experimental set-up limited the position of the hot wires
ii-
to the outside of the propeller shafting. Consequently, when the data for
Experiment 3 was transposed to the starboard side, there was no model data
between 0 and 100 degrees. This transpositiou was required to compare the
wind tunnel model data to the full-scale data which was available only
on the starboard side of the R/V ATHENA.
A study of the full- and model-scale velocity component ratios presented
shows that tne data agreement is acceptable. Comparison of the data from
the wind tunnel transverse wake surveys reveals that there is little
significant difference between measurements made ahead of the propeller
plane with and without an operating propeller. Differences in the wake
with and without the propeller operating are within experimental accuracy.
From these wake survey experiments, the effect of an operating propeller
is not measurable at 1.11 diameters forward of the propeller disk.
ROTATIONAL WAKE SURVEY EXPERIMENT
Model-scale wake surveys were performed in the wind tunnel to correlate
the data obtained from the full-scale and model-scale towing tank experi-
ments. The wake survey experiment in the towing tank was performed by
towing the model at the Froude-scaled speed of the ship. The wind
tunnel rotational wake survey was conducted on the double model
in the propeller plane at a Reynolds number corresponding to the Froude-
7scale speed of the towing tank experiment, R n 1.56 x 10 . Measurementsn
made at the same nondimensional radii as used for wake surveys on the
R/V ATHENA and the towing tank model, Model 5365, were 0.456, 0.633,
0.781 and 0.963 as listed in Table 1. The results of this wind tunnel
experiment are presented in Appendix B for the experimental radii. A harmonic
12
~.- 'e
analysis was performed on the longitudinal and tangential velocity
component ratios. The advance angles were calculated using an advance
coefficient, JV, of 0.739. Circumferential mean velocity component
ratios, volumetric mean velocities and the advance angles are presented
graphically and in tabular form in Appendix B. The harmonic content
of the circumferential distribution of the longitudinal and tangential
velocity component ratios at the experimental and interpolated radii
is presented also in Appendix B.
The data from the wake surveys in the towing tank and wind tunnel
are shown in Figures 28 -nrough 31 along with the full-scale data. The
velocity component ratios presented in these figures showed that the
degree of scatter of the full-scale data was higher than that of the data
from the two model experiments. The rotational wake survey data obtained
in the wind tunnel showed very little scatter when compared to the towing A
,ank data. The longitudin-1 velocity component ratios of the wind tunnel
Model 5366 were 5-to-lO percent lower than those of the towing tank Model
5365. The tangential velocity compop-.n ratios for Model 5366 at radius
ratios of 0.456 and 0.781 were 2-to-5 percent higher than those for Model
* 5365 from 0 to 350 degees. The radial velocity component ratios of Model
5366 were 2-to-8 percent higher than Model 5365 from 180 to 360 degrees
for all four radii. The tangential and radial velocity component ratios
for radius ratios of 0.633 and 0.963, were similar at angles between
0 and 180 degrees.
The results from model wake experiments in the wind tunnel and in the
towing tank indicated significant differences. The greatest variation in
the data was ten percent in the longitudinal velocity component ratio
13
Afta>
i /;.... ........ ... n.. .. *...-' - Al.." . . . C. , " ' ' i
for the innermost radius. The large values of the towing tank data, which
were consistent with other R/V ATHENA model experiments, may be due to the
inability of the pitot tube to measure velocities at large flow angles.
At the outer radii, the longitudinal velocity component ratios for the
ship were l-to-2 percent lower than those for the model in the wind Atunnel. The peaks of the radial and tangential velocity component ratios
at the outer radii were 8-to-10 percent higher for the ship than for the
double model. At the two innermost radii, the shift in the radial and
tangential velocity component ratios indicated that there was a strongerupflow on the ship than the model, in the region under and outboard of the,
propeller hub.
Comparison of the full-scale and wind tunnel model wake revealed
differences up to 10 percent. The full-scale data showed the largest
scatter and the greater deviation from the model-scale wake.
STRUT WAKE EXPERIMENT
The transverse wake survey experimental set-up also enabled measure-
ments to be taken behind the struts with an operating propeller. The
S. purpose of this experiment was to numerically determine the velocity
decrement due to the struts with an operating propeller. Finely spaced
measurements were taken transversely behind the struts. Measurements
were made between the shafting and the hull surface at 57, 76,and 95 millimeters
from the shaft centerline. Figure 32 presents the results of this experi-
ment.
For the measurements obtained at 57 millimeters from the shaft center-
line, a 5-to-10 percent variation in the longitudinal velocity 2components was seen in the area immediately behind the struts. This
14
variation was not observed at the other two locations from the shaft
centerline. At the two innermost radii of the rotational wake survey, the
longitudinal velocity components showed a 10 percent velocity defect which
was consistent with the results from the strut wake experiment.
CONCLUSIONS
Model-scale boundary layer velocity profiles obtained one propeller
diameter ahead (Locations 1 and 8) and astern (Locations 3 and 7) of the
propeller plane, were 2-to-10 percent smaller than the full-scale profiles.
This difference was caused by the one decade reduction of the model-scale
Reynolds number, as compared to the full-scale Reynolds number.
However, in the area where the shaft bossing pierced the hull, the
model- and full-scale boundary layer profiles coincided. Further investi-
gation on the model-scale data yielded no unusual flow phenomena in this
area. It is recommended that additional experiments be conducted to
understand this phenomena.The propeller caused a 1 percent increase in velocity in both the
7 model- and full-scale boundary layers at Locations 1 and 8, one propeller
diameter ahead of the disk. At Locations 2 and 6, where the shaft bossing[pierced the hull, there was no measurable difference in the data obtainedwith or without the propeller operating.
Wake survey experiments ahead of the propeller plane were intended to
provide a comparison of velocitv components with and without the propeller
operating. When the suatter .i. values is taken into consideration, it is not
possible to discern any significant difference between the two sets of data.
Wake measurerments ahead of the propeller plane without the propeller oper-
ating showed only a 1 percent radial decrease in the volumetric mean wake
as compared to measurements made with the operating propeller.I 154 4
-~ >
' •' t
Behind the struts in the propeller plane, at a r/R of 0.287, a ten
percent velocity defect in the longitudinal component was seen when
compared to free stream velocity. This agreed well with the results from
the rotational wake survey and also the towing tank wake surveys at a
similar radius.
Experiment 5, the wake survey conducted in the propeller disk, was
performed at the same Reynolds number as those experiments done in the
towing tank. The longitudinal velocity components fromi the wind tunnel
experiments agreed better with the full-scale data than with the towing
6tank data. As mentioned by Reed and Day, the discrepancy between the
towing tank and full-scale data may be due to the difference in attitude
between the ship and model. The wind tunnel double model was constructed
to take into account the dynamic trim of the full-scale ship, so that an
error in attitude is unlikely.
Overall, the longitudinal velocity component ratios obtained in the
wind tunnel correlated better with the full-scale data at the inner radii.
The tangential and radial velocity component ratios were generally higher
for Model 5366 than for the towing tank data. The radial and tangential
components from both models seemed closer to each other than to the
full-scale data.
Hot wire anemometry enabled the measurements of model-scale boundary
layer profiles and nominal wakes in the wind tunnel. A hot wire system
has not been used in the towing tank to measure borndary layer profiles at
DTNSRDC, and a pitot tube system has not been used to obtain data ahead of
the operating propeller. It is felt that with further experiments with
hot wire anemometry, measurements in the wind tunnel would provide a valuable
technique in determining the wake and boundary layer of surface shipa.
16
* ~ 4
WI
REFERENCES
1. Brownell, W. F., "An Anechoic Flow Facility Design for the NavalShip Research and Development Center, Carderock," NSRDC Report 2924(Sep 1968).
2. Bowers, B. E., "The Anechoic Flow Facility - AerodynamicCalibration and Evaluation," DTNSRDC Ship Acoustics Department EvaluationReport SAD-48E-1942 (May 1973).
3. Scragg, C. A. and D. A. Sandell, "A Statistical Evaluation ofWake Survey Techniques," International Symposium on Ship Viscous Resistance,SSPA, Goteborg, Sweden, pp.8:1 - 8:14 (1978).
4. Grant, Jerald W. and Alan C. M. Lin, "The Effects of Variationsof Several Parameters on the Wake in Way of the Propeller Plane, For Series60-0.60 C Models," NSRDC Re2search and Development Center, Report 3024(Jun 1969 .
5. Hadler, J. B. and H. M. Cheng, "Analysis of Experimental WakeData in Way of Propeller Plane of Single- and Twin- Screw Ship Models,"Trans. Soc. Naval Arch. and Mar. Eng., Vol. 73, pp. 287-414 (1965).
6. Reed, A. M. and W. G. Day, "Wake Scale Effects on a Twin-ScrewDisplacement Ship," Twelfth ONR Symposium on Naval Hydromechanics,Washington, D. C. (1978).
17
k °
WWSHIP AND MODEL DATA FOR R/V ATHENAREPRESENTED BY DTNSRDC MODEL 5365 AND 5366
Appendages: Shafts, V-Struts, Rudders, Centerline Skeg, Stabilizer Fins
Ship Model
Length Overall 50.3 m 6.10 mLength on Waterline 47.0 m 5.70 mLength Between Perpendiculars 46.9 m 5,69 mBeam (Maximum) 6.68m 0.81 mDraft (Mean) 1.715m 0.208mDisplacement 266 t 240.463 mJWetted Surface 317.1I 4.66
Coefficients
Scale Ratio = S/LM 8.25Block Coefficient CB 0.48Prismatic Coefficient CP 0.63Length/Beam Ratio L/B 7.04Beam/Draft Ratio B/T 3.89Displacement/Length Ratio 6 7.15
717
o.6
0°0.2
A.P. 18 16 14 12 10 8 6 4 2 1.P.STAT 10.W
-- 7 -" --. ,-*-'---A ,Z ,.T -__,__.,2
3 2 1 -..
A.r. 19 18 17 16
Figure 1 - Ship and Model Data for R/V ATHENA Represented by Mordls: 5365 and 5366
18
, -
J .1d; J 3 '"
*~" 00 9-
C;8 0
* 0.014
* .0 . - I.V* 00 v-
d.0' d d d-4
±0.19
rill- --77F
T-4
0 c
4)
41
4) 4
00
zH
00
Ce')
-to
IlIt--
00 .- '
20
20 19 18 SHEER
D.W.L.r
LONGITUDINAL POSITION PLANE OF TRANSVERSE WAKEOF STRUT WAKE SURVEYS AT FORWARD RAKEMEASUREMENTS LOCATION EXPERIMENTS 2 8 3,EXPERIMENT 4, x/LwL = 0.938 x/LwL = 0.906
ROTATIONAL WAKE SURVEYPLANE EXPERIMENT 5,x/LwL = 0.949
Figure 4a - Longitudinal Locations of Wake Survey and StrutWake Measurements on Model 5366
10 20
,"' - D.W.L.
. VERTICAL SPACING IS 25.4 mm
F!Figure 4b - Ttansverse Grid Locations of Measurements of Experiments 2 and 3
21
° , ,'.'
C; C-
4- 4
0 C)
4 'CV
Ifl fAl CLO
o o c 0:~
440
CCi2
co
1
44 .
22w
I PSD 54~9-15A
?igure 6 -Double Model Installed in DTNSRDC Wind Tunnel forBoundary Layer and Rotational Wake Survey Experiments
PSD 520-5A
Figu~e 7 -Double Model Installed in DTNSRDC Wind Tunnel for
Transverse Wake Survey Experiments
23 I
PSD 548-
Fiur 8 xeietlStU o Budr ae xeiet
PD 5I8-A
Figure 8 Cleuperimenta Seof Boundary Layer eins
24I
j 2v
PSD 548-18A
Figure 10 Close--up View of Boundary Layer Probewith Opersting Propeller
PSD 5h9-11A
Figure 11 - Single Sensor Hot Wire Anemometer ProbeUsed for Boundary Layer Profile Measurements
PSD 520-13A
Figure 12 - Experimental Set-Up for Transverse Wake Surveyand Strut Wake Measurements
25
-7I
Figure 13 - Triple Sensor Hot Wire Anemometer Probe
Used for Wake Survey Measurements
PSD 1009-78-11
Figure 14 - Hot Wire Probe Mounted with Drive Motorfor Rotational Wake Survey Experiment
26 j
IIII
Velocity Profile Data from R/V ATHENA and Wind Tunnel Model 5366 at
Locations 1 and 8 x/LL - 0.90
MODEL SCALE U. = 45.7 m/s, Rn- 1.68 x 107
0 3 WITHOUT PROPELLERE WITH PROPELLER
E i SPIP SCALE U. - 7.6 m/s, Rn- 4.14 x 10W, 0 WITHOUT PROPELLER
400 ')WITH PROPELLER
-40 (_ _
0s o
hA
43000
200 -J3:
0
2O
200
W: >
00 00 00
U/Uo " Uo = SHIP, MODEL SPEED
Figure 15 - Measured Boundary Layer Velocity Profiles for R/V ATHENA
and Wind Tunnel Model 5366 with and without Propellerat LocaL.ons 1 and 8
27
$[
Velocity Profile Data from R/V ATHENA and Wind Tunnel Model 5366 at
Locations 2 and 6 x/LW = 0.77
E MODEL SCALE U. -45.7 a/*, Rn, 1.68 x 10 7
E E 0WITHOUT PROPELLER
E 1 0 WITH PROPELLER.j SHIP SCALE U. - 7.6 rns, Rn - 4.14 x 10 8
W 9 0 WITHOUT PROPELLER
............... .......................--- ~ -~ - - ~-U "j
0 50 - ......
400
W
, 40 ...... ..
"300 _j[3
30
0
200 0
Z 20 " ',
100 -,
0
o 0 1 ---02 04 06 08 1.0 12
U/Uo " Uo SHIP, MODEL SPEED
Figure 1C - Measured Boundary Layer Velocity Profiles for R/V ATHENA
aud Wind Tunnel Model 5366 with and without Propeller
at LocaLlons 2 and 6
28
Velocity Profile Data from R/V ATHENA and Wind Tunnel Model 5366 at
MO)DEL SCALE Us - 45.7 mn/9, R u1. 68 x 107
E 0 WITHOUT PROPELLERI E E 'o WITH PROPELLER8
Ew SHIP SCALE U. - 7.6 m/s, R *4.14 x 108II n-j 0 WITHOUT PROPELLER
W * WITH PROPELLER
U,
50
40 0 wW
D 40___ _
-300 _, *
-J
30
(00200
w
z 20_
I10(0
0
0 0 02 04 06 0.8 1.0 1 2
U U 0 Uo SHIP, MODEL SPEED
Figure 17 -Measured Boundary Layer Velocity Profiles for R/V ATHENAand Wind Tunnel Model 5366 with and without Propellerat Locations 3 and 7
29
1 ,1 .4,,44 ~ ~ v, •
1,' 1-3 t; - 2_ -2 -) .3 -3 % 37 - 3IN,j . -.. . . .... .. .... . . .. . - . - .
f5
I
C. lI E 'N "[;.RE
o FULL SCALE DATAMODEL SCALE DATA - EXPERIMENT 2
Figure 18 - Velocity Component Ratios for R/V ATHENA and Model 5366 at the
Forward Rake Location (x/LWL - 0.906) with an Operating
Propeller for the 0.417 Radius
30 14.- '.
0 -3.W
1.-------------------------------------------- -+------------
0 . 1 - . --.
0 FUL SCALE DA
P 0.f -
311
04l
0 I -+., .. ,-4
"> E."C.'mE -,
E-: o FULL SCALE DATA+ +- MODEL SCALE DATA -- EXPERIMENT 2
Figure 19 - Velocity Compont..it Ratios for R/V ATHENA and Model 5366 at theForward Rake Location (x/LWL - 0.906) with an OperatingPropeller for the 0.583 Radius
31 1
-.-- , -: -+ ?..: -.. _ ....
L, I
0 3
3--
03---
>S
10 . 1 120 1 40 ,._ ' 3
" FULL SCALE DATA+ MODEL SCALE DATA -EXPERIMENT 2wihaOprtn
Figure 20 -Velocity Component Ratios for R/V ATHENA and Model 5366 at theForward Rake Location (x/LWL .0'wtha prtnPropeller for the 0.750 Radius
.LI32
_0
0.- -- 4
0.-
0.3.3-.
-3 1
_lie__
-04
-0C
_20 :J 20 40 50 3 10 10 6 I S 20 2024 26 230 09U 3035 39
-0.2 ~ ~ ~ ~ ~ iNL -N -DEGREES--- - -- -- - -- -
o. F- - - - - - - - - - - - - - - - - - - - - - - -
MODEL~444 -CL DATA EXEIMN
Figure----------~ 21 Vlct opnn Rto o / TEA n oe 36a h
0-rar RaeLcto-xLL=096 iha prtnPropeler fr the0.917Radiu
~0.1 - - - - - --. -33
* ' M64
t) 3
I4
-2 0 C 3 0 1CI - 0 2 4 6 .3O 30 3" 30R I E N EZGE
1.1LSAL DT
34---
..... .... 1
IQI01.2 -
U-1.310--
9... 1 .......
0?-, -,,, --
*0-0
-02
-2 0 4 0 3 10 10 010 19 20., 22 " " '6 23 "'-. 340 3
-. , ..,-, ..... .'-.-..-
PNGrLE TN IDECREES
CFULL SCALE DATA+ MODEL SCALE DATA ~-EXPET1MNT 3
Figure 23 Velocity Component Ratios for RIV ATHENA and Model 5366 at theForward Rake Location (x/LWL 0.906) without an OperatingPropeller for the 0.417 Radixis
35
V -
1..-
0.8--
, 7
0 6
0.
0.3
0.3 .,
-000'- --
02---- - -- ., .
-" 0 1 - , .I I" "
-0 ) )... :,,, .. ... ,. . .,.SELI
NGLE IN DEGREES
e FULL SCALE DATA+ MODEL SCALE DATA -EXPERIMENT 3
Figur 24 Velocity Component Ratios for R/V ATHENA and Model 5366 at the
Forward Rake Location (x/LWL = 0.906) without an OperatingPropeller for the 0.583 Radius
36
r*.
.5.,- ... - .,+.. .. . . ++ +
,:+ .. -02-:+'+. ..+ d+,+;- . .:L., :: :.+::, ..... ... .. - - 'I .... .+.,++ .: ++ +:
0.6-
I~~~ -7~--
0- -- - - - -
01-----------------------
05 3~
-0- - - ~ -
-20 0 20 40 60 5 0 100 120 14 0 1 60 ' 90 200 2 20 "A0 260 290 300 320 340 3q' 39
RNGLF. TN OE.CREE5
o FULL SCALE DATA
Figure 25 -Velocity Component Ratios for RIV ATHENA and Model 5366 at the
Forward Rake Location (x/LWL = 0.906) without aai Operating
Propeller for the 0.750 Radius
37
'r ' I 57T
08
0.3
N 0 0---- - A
-o ~. - - -
-20. i 06C9G101010I3 9 0 10LA 6 8 0 2 4 5 9
-02- ---- -, -EGE.
FUL SCAL DATA-
MOFULL SCALE DATA EPRMN
Figure 26 -Velocity Component Ratios for R/V ATHENA and Model 5366 at the
Fo-ward Rake Location (x//LWL 0.906) without an Operating
Propeller for the 0.917 Radius
38
k i"'At A
1.1
1 -
0* . .'...."
0.6
03
0 6 -C . .. 120 14 1
0 i -," ), ... ,..-,. -"
-0 0 :0 .... -"
-02 -
Forar Rak Loain(x--0.0)wthu-nOprtn
'01
I .-... ... ''-
-20 0 20 d40 60 '3C 100 120 l.40 160 1''., 200 220 2dO 260 260 300 320 3,'0 3 ;0 3']C
ANGLp fN OEGRE1.S" FULL SCALE DATA~+ MODEL SCALE DATA - EXERl4ENT 3
Figure 27 - Velocity Component Ratios for R/V ATHENA and Model 5366 at the
Forward Rake Location (x/LWL - 0.906) without an Operating IPropeller for the 1.083 Radius
39I
X. '. X X )x x JX 01R -L2 "'x )I
3 3 - "o -"°XX
03 1 0 _
X 0
0 FULL SCALE DATA
34 ------------------U A
0- o-o
0.-- t O I 0~ -0~:
"3 2* q0v 0'))
-0 I v ...
:c= 0I-20 0 20 40 60 9C iC0 120 140 160 1C 200 220 20 260 29G 300 320 340 330 3032
ANGLE IN OEGREES
x VELOCITY COIPONENT RATIOS FOR MODEL 5355 TOWING TANK- VE OC ITY COMPONENT RATIOS FOR MODEL 5356 WINID TUNNEL
Figure 28 - Composite Plot of Velocity Component Ratios for R/V ATHENA andModels 5365 and 5366 at the Propeller Rake Location (x/L-L 0.949)for the 0.456 Radius
40
S XX1 X X x o
1;--< ~.eel 1+1.++j+.*~1. 1 H~
0 r 1 ULSCALEDA.
0.3 --_
00
>~<. 1- ,~,. '
-2 040 60 1C 100 120 140160O 1'30 200 220D 240 260 2190 300 3ZO 340 330 313CFNGLE IN DECREES
x VELOCITY COMPONENT RRTICJ$ FOR MODEL 5365 TOWING TANK+ VE[OCITY COMPONENT RRTIOS FOR MODEL 53S6 WIND TUNNEL
Figure 29 -Composite Plot of Velocity Component Ratios for R/V ATHENA andModels 5365 and 5366 at the Propeller Rake Location (x/LWL 0.949)for the 0.633 Radius
41
x 1.1- xi - -> x YxrI x 1 bxg x -~
0.9 ,
0.5
0- FULL SCALE DATA.
I0.40.3 -4
5- --
I-W -
0.20
0 1 ~ _
xx
-20 0 2 0 40 r)0 930G 100 120 140 160 190 200 220 240 260 280 300 32-0 340 3630 310
x VELOCITY COMPONENT RRTIOS FOR MODEL 5365 TOWING TANKVELOITYCOMONEN RnIOSFOR IIOOE. 5366 WIND TUNNEL
[Figure 30 -Composite Plot of Velocity Component Ratios for R/V ATHENA andIModels 5365 and 5366 at *the Propeller Rake Location (x/LWL 0.949)V for the 0.781 Radius
I 42
x x X1 OK) X -4p X CXXC
0 7
0 FULL SCALE DATA
Q P
-01 - .0 - - - -0
02-
-20 0 2 dO ~0 0 '00 120 140 11;0 1130 200 220 2d0 260 200304 6 9
RNGLE TN DEGREES
x VELOCTTY COMPONENT RRT133 FOR MODEL 5355 TOWING TANK
q EL OCT TY COMPONENT RRT!OS FOR MODEL 5366 WIND TUNNEL
Figure 31 -Composite Plot of Velocity Component Ratios for RIV ATHENA and 4Models 5365 and 5366 at the Propeller Rake Location (xILWL 0.949)for the 0.963 Radius11
43I
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Ii APPENDIX ASIVELOCITY COMPONENT RATIOS AND HARMONIC ANALYSIS OF THE TRANSVERSE
SWAKE SURV',ZY EXPERIMENTS WITH AND WITHOUif AN OPERATING PRO±PELLER
~, I
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6^ ?C300 320 ,4) 3r.0 31J
RNGLE IN DECREE.S
x Model 5366 Transverse Wake Survey Experiment 2 with PropellerModel 5366 Transverse Wake Survey Experiment 3 without Propeller
Figure A-3 - Composite Plot of Velocity Component Ratios from theTransverse Wake Surveys at the Forward Rake Locationfor the Interpolated Radius of 0.781
49
as:~ ~ 2~1" -
U !
"-"X O .''.k..:
1 *
-- 4
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-2 20 4, A, ?c 10C '20 140 ?r"c ''0 200 220 ?40 253 200 ?GC ?20 31!0 3%
RN CI-F T N DLE E
K Model 5366 Transverse Wake Survey Experiment 2 with PropellerModel 5366 Transverse Wake Survey Experiment 3 without Prcpe2ler
Figure A-4 Composite Plot of Velocity Component Ratios from the
Transverse Wake Surveys at the Forward Rake Locationfor the Interpolated Radius of 0.963,
50 1
44,.(
X ^' -
1.o - - - - * - - - -.. . - - -,, . -;4 -J - - , - -%,
1.I . .1
)<'
x Kx
0 7
0 3
0 2 -- Q4 4
-01 -- .
IIRAOIUS
0D 19 <A>EXPERIMENTAL RADII
X INTERPOLAT.D RADII
Figure A-5 - Radial DistrIbution of the Mean Velocity Component RaLosfrom the Transverse Wake Survey at the Forward RakeLocation with an Operating Propeller
51
_ 1,4'$. k*~ & ( -. . ~ .r
40
x
30 I0
x
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X INEPOAE RAI
3-- .... -4
O<).L EXPERIMENTAL RADII- - -----
-- X INTERPOLATED RADII -- -1I0
. ....- -- -12
I I{I
Figure A-6 - Radial Distribution of the Mean Advance Angle and Advance
Angle Variations from the TrAnsverse Wake Survey at theForward Rake Location with an Operating Propeller
52
! I .-- 1l. 2-- 1 .
>x x x
06 0 .
x
0.,1o
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0---- -- - - --RIENTA RADIII
0 '3-----------------------------------
o--07 0. 3
: > x xx
-0 -- -0
II
-). - .0 1 .... 1 1 -
0.3 0. M 0.i 0.6 0.7 01..
RAOIUS
Figure A-7 - Radial Distribution of the Mean Velocity Component Ratios
from the Transverse Wake Survey at the Forward Rake
Location without an Operating Propeller
53
40
30 10
" Xxx
20 x X x'
x
X -.4
t C)
F) W-Oi A EXPERIMENTAL RADII -1
X INTERPOLATED RADII- - - - --- 10
0 0F0RD0 '.0 I. 1.2
A Dl I US
Figure A-8 - Radial Distributitn of the Mean Advance Angle and AdvanceAngle Variations from the Transverse Wake Survey at theForward Rake Location without an Operating Propeller
54
M. C l v' 0 C'(,0 0I 4,
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SPACE IS "L ~bII
55
'CiA
7
INS
TABLE A-2Ii HARMO~gNIC ANALYSES OF LONGITUDINAL VELOCITY COMPONENT RATIOSAT THE EXPERIMENTAL AND INTERPOLATED RADII OF THE TRANSVERSEWAKE SURVEY WITH AN OPERATING PROPELLER
HARMONIC = 1 2 3 5 6 7 a
RADIUS = .456AMPLITUDE .0154 .0061 .0106 .0101 .0076 .0027 .0021 .0019PHASE ANGLE 331.2 355.1 217.{; 27,1.3 322.2 291.2 216.4 298.3
RADIUS = .633AMPLITLUDE T .0357 .0151 .0 192 ,0I'll .0122 .0033 .0034 .oc2)PHASE ANGLE = 299.9 311.8 2(,b.7 277.4 317.2 337.2 224.J 317.3
RADIUS = .781AMPLITUDE .0674 .0368 .0247 .U2l7 .0121 .0054 .0029 .0014PHASE ANGLE 292.2 302.1 2i4. 1 2813 8 335.4 44.8 200.4 29.3.6
RADIUS r .963AMPLITUDE .1218 .0820 .u(439 .02,9 .0163 .0127 .0102 .00,11PHASE ANGLE x 288.7 301.4 302.3 314 4 356.1 79.4 111.3 2.0
RADIUS = .312AMPLI1UDE .0137 .0091 .0.02 .00'R .0054 .0017 .0020 .0031,PHASE ANGLE 3 2.2 345.4 1'19.0 51.2 54.6 167.1 113.3 247.9
RADIUS = .417AMPLI1UDE .0139 .0063 .00t 1 .00,1 .0060 .0021 .0016 .0020PHASE ANGLE 342.1 359.3 212.9 277 6 3342.4 279.7 202.4 2 '2.0
RADIUS = .583AMPLITUDE .0279 .0106 .017, .01.3 .0116 .0034 .0033 .0025PEASE ANGLE x 305.2 320.1 21,0.3 27$ 2 3 -,.3 320.1 226.1 320.1
RADIUS = .750AMPLITUDE - 0598 .0311 .0229 .rt2.2 .0118 .0046 .OOJ2 .00,13PHASE ANGLE 293.2 302.9 200.0 2U'5 5 3-1.2 34.2 215.,1 292. 0
RADIUS -, .917AMPLI IUDE .1064 .0616 .03, .0 'O .0147 .0105 .00(3 .00 4'PHASE ANGLE 289.3 301.3 2 8.y c7.4 351.9 73.5 119.6 :' .s.',
RADIUS r 1.083 2
AMPLITUDE .1218 .0820 .04 3,1 .02.,) .0163 .0127 .0102 .0011
PHASE ANGLL 288.7 301.4 302.3 31-1.4 356.1 79.4 111.3 2.0
56
| I. il I
TABLE A-2 CONTINUED
MODEL 5366 TRANSVERSE WAKE SURVFY EXP 2 WITH PROPELLER
HARMONIC ANALYSES OF LONGITUDINAL VELOCITY COMPONENT RATIOS (vx/V)
HARMONIC 9 10 1 1 12 13 14 15 16
RADIUS = .456
AMPLITUDE .0013 .0008 .0009 .0011 .0001 .0004 .0002 .0004
PHASE ANGLE x 324.3 135.5 192.2 251 4 330.3 123.2 225.2 73.6
RADIUS = .633
AMPLITUDE .0041 .0005 .0024 .0o.'s .0014 .0005 .0009 .0007
PHASE ANGLE 351 .2 104.3 210.,1 270.7 302.8 99.6 181 .9 222.9
RADIUS = .781AMPLITUDE .0058 .0008 .0011 .oo 79 .0027 .0015 .001 .0011,HASE ANGLE 345.4 324.3 213.0 2,,3 3.9 103.3 183.5 269."
RADIUS = .963AMPLITUDE .0071 .0049 .0021 .0010 .0019 .0019 .0027 .0018PHASE ANGLE 6.2 79.0 138.5 298 1 353.0 128.0 199.6 2(-b. i
RADIUS = .312AMPLITUDE .0029 .0006 .0.0112 .00.1 .0032 .0012 .0005 .0017
PHASE ANGLE 220.5 214.9 t,8.o 96.9 74.0 123.4 291.0 17.2
RADIUS = .417
Ar.:PLI TUDE .0010 .0007 ."005 . 00'1 .0006 .0005 .0002 .000,
PHASE ANGLE 265.8 145.9 1;7.O 223.15 70.3 124.8 257 .J .17. R
RADIUS r .583AMPLITUDE .0034 .0007 .0020 .003 .0012 .0003 .0007 .00')5
PHASE ANGLE 350 13 115.5 2,0.6 2,6.9 289.0 102.1 1H3.9 197.7
RADIUS = .750AMPLITUDE (. .0008 .00'1 . oh*" .C024 .0014 .00(1 .001PHASE ANGLE 344.4 308.8 214..o 289 2 .5 101.1 181.8 267.7
RADIUS = .917
AMPLITUDE .0067 .0029 .02C0 .005 .0024 .0019 .0024i .001o
PHASE ANGLE 358.8 71.6 riJ.3 ."1 '.8 2.2 119.5 194.11 2(,9.4
RADIUS = 1.083AMPLI ILIDE .0071 .0049 A021 .00 0 .0019 .0019 .0027 .0018PHASE ANGLE 6.2 79.0 1.. ',8.1 353.0 128.0 199.b 26b.8
57
$t~t . .7
I%
TABLE A-3
HARMONIC ANALYSES OF TANGENTIAL VELOCITY COMPONENT RATIOSAT THE EXPERIMENTAL AND INTEP2OLATED RADII OF THE TRANSVERSEWAKE SURVEY WITH AN OPERATING PROPELLER
HARMONIC = I 2 3 4 5 6 7 8
RADIUS = .456AMPLITUDE = .1678 .0129 .0,302 .01b2 .0074 .0094 .0047 .o01IPHASE ANGLE 184.7 152.5 8.4 304.9 28.0 47.9 8.5 130.3
RADIUS = .633AMPLITUDE .2059 .0197 .036,1 .0102 .0040 .0083 .0025 .0016P11ASE ANGLE 179.1 24J.2 358. 1 6.4 351.0 29.5 46.6 287.6
RADIUS = .781AMPLITUDE .1850 .0181 .0392 .01,4 .0009 .0067 .0035 .0022PHASE ANGLE 183.4 306.3 7.5 38.3 305.5 33.0 75.9 256.5
RADIUS = .963AMPLITUDE 2 .1544 .0459 .0421 .0 '9 .0061 .0046 .0023 .0013PHASE ANGLE z 197.6 339.3 8.7 10.7 349.6 70.1 148.4 161.4
RADIUJ = .312AMPLIIUDE z .1006 .0464 .1,293 .02. 3 .0125 .0116 .0082' .00'0PHASE ANGLE = 213.0 84.0 ,11.9 2lI . 53.6 74.1 . 134.7
RADIUS .417 i1.$ 536 7 .11 ,4 7
AMPLITUDE .1510 .0173 .02H9 .01,2 .0085 .0097 .005 .0021PHASE ANGLE 188.5 120.0 15.2 a,., 3 35.8 54.6 5.0 131.3
RADIUS = .b83AMPLITUDE .2021 .0185 .0349 .01 2 .0049 .008q .0027 .0012PHASE ANGLE 179.4 227.5 3"6.3 ,3,Ip 3 1.1 32.5 31.4 295.2
RADIUS = .750.IPLITIMDE .1899 .0160 .3 jr .0113 .c009 .0071 .00 i .00?2
VHASE ANGLE 1s2.1 292.1 6.3 36 9 J13.5 31.1 71.0 243.0
RADIUS - .917AMI LITUDE .1619 .0373 .0415 .0l 15 .0038 .0049 .002.1 .0011)PHASE ANGLE 192.8 p35.8 9.,j 22.1 344.9 55.2 116.0 196.2
RADIUS = 1.083AMP LII UDE z .1544 0459 .0421 .0159 .0061 .0046 .0023 .0013PHASE ANGLE = 197.6 339.3 8.7 10 7 349.6 70.1 148.4 161.4
I
58
i !I
TABLE A-3 CONTINUED
MODEL 5366 TRANSVERSE WAKE .,URv,'Y EXP 2 WITH PROPELLER
HARMONIC ANALYSES OF TANGENTIAL VElOCITY COMPONENT RATIOS (VT/V)
HARMONIC = 9 10 11 12 13 14 15 16
RADIUS = .456rAMPLIIUDE .0039 .0011 .0020 .0024 .0008 .0025 .0013 .0019PHASE ANGLE = 144.2 104.9 C5.9' 127.6 116.0 132.4 116.3 126.5
RADIUS = .633AMPLITUDE ..0012 0017 .0020 .003 .0020 .0007 .0016 ,0011
PHASE ANGLE 17.9 97.4 317.8 3b5.5 160.6 121.2 146.6 218.2
RADIUS = .781AMPLITUDE .0018 .0036 .0012 .0008 .0022 .0011 .0017 .0013PHASE ANGLE x 356.1 73.6 120. t3 ,47.0 107.4 100.6 S5.0 119.u
RADIUS = .963AMPLITUDE .0045 .0063 .0045 .0017 .0052 .0043 .0026 .',PHASE ANGLE 135.3 136.6 1. 4 1 :8.1 130.7 138.2 123.6 119. "
RADILS = .3122AMPLITUDE .0107 .0020 .0,1' . ' 9 .00,10 .0056 .001,( .00'0PHASE ANGLE 152.5 65.8 1C.7 11 3 1(2.6 130.5 36.7 12. , •
RADIUS = .417AMOPLITUDE .0055 .0049 .0Oj .00,9 .CC1 .0032 .001, .0C2c
" -
PHASE ANGLE . 147.9 94.3 IJ0 .7 113 ,, 65.2 132.0 9 . 9 113.
RADIUS = .583AMPLITUDE .0008 .0014 .v0Ip .0019 .0018 .0010 .0026 .0011
PHASE ANGLE = 69.0 106.6 33.4 t'.6 I ,.0 129.1 150.1 210.3
RADIUS = .750A
AMPLITUDE = .0020 .0034 C-0Ou q . 0 9 .0019 .0009y .0015 .0010|
PHASE ANGLE = 352.7 69.5 10 .7 0 3 109.0 92.6 57.9 12e.3
RADIUS = .917 ,
AM PL I TUDE = .0023 .0049 .LO 7 .0 0 -2 Q .0041 .0031 .0020 .00"2 I
P"SE ANGLE = 124.6 119 5 IJ5.7 1P3.5 129.6 132.7 98,t 1 15 '
i
RADIUS = 1.083 ,
AMPLITUDE = .0045 .0063 .0045 .00 17 .0052 .004-1 .0026 .00,"5
PHASE ANGLE = 135.3 136.6 138.4 12;,_1 1-,0.7 138. "2 123.6 1 19.-1
• ':, i :: '2'
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60
ii
TABLE A-5
HARMONIC ANALYSES OF LONGITUDINAL VELOCITY COMPONENT RATIOSAT THE EXPERIMENTAL AND INTERPOLATED RADII OF THE TRANSVERSEWAKE SURVEY WITHOUT AN OPERATING PROPELLER
HARMONIC 1 2 3 4 5 6 7 8
RADIUS .456AMPLITUDE .0287 .0131 .0,1,15 .01 "1 .0117 .0065 .0034 .00:34PHASE ANGLE s 314.7 69.3 243.7 293.0 348.3 56.4 189.6 283.3
RADIUS = .633AMPLITUDE .0454 .0109 .OlI3 -02.,8 .0182 .0089 .00b) .00 '2PHASE ANGLE 301.8 10.8 2.18.5 288.3 34J.6 67.0 203.3 292.6
RADIUS z .781
AMPLITUDE .0622 .0231 .0211 .02.45 .0201 .0145 .0107 .0139PHASE ANGLE 306.1 307.9 275.S 300.1 357.8 85.7 190.6 287.2
RADIUS = .963
AMPLITUDE .1253 .0634 .0362 .0303 .0174 .0188 .0127 .00',6PHASE ANGLE = 288.4 316.7 321.2 316.6 6.5 94.0 148.7 301.9
RADIUS = .312AMPLITUDE .0262 .0094 .0106 .01)3 .0076 .0070 .0051 .0031PHASE ANGLE 355.4 101.0 2ds.1 3.10.0 55.6 78.0 115.2 1722
RAIIUS = .417AMPLITUDE .0262 .0128 .0131 .01.7 .0097 .0063 .003 .0023PHASE ANGLE 323.1 76.3 2.18.' 2,)9.2 3513.4 59.5 176.4 267.1
RADIUS = .583 'AMPLITUDE .0403 .0112 .0176 .02' 3 .0169 .0079 .0051 .0076PHASE ANGLE 302.5 35.2 2.13.7 27.2 3,42.0 61.0 205.J 293.1
RADIUS = .750AMPLITUDE .0565 .0183 .020.1 .0?'? .01)9 .0134 .00. .0138PHASE ANGLE 307.9 310.2 2(7.( 2'7 5 355.6 83.3 194., 287.3
RADIUS = .917AMPLITUDE = .1040 .0511 .0302 .02')q .0187 .0181 .0tl) .00(1PHASE ANGLE 2 292.7 313.5 311.5 J2 2 4.7 92.4 162.3 292.3
RADIUS -- 1.083
AMPLITUDE z .1253 .0634 .03t,2 .0303 .0174 .0188 .0127 . 0o0'PHASE ANGLE x 288.4 316.7 3:'1.2 J16.6 6.5 94.0 148.7 301.9
61
61
i.-
TABLE A-5 CONTINUED
MODEL 5366 TRANSVERSE WAKE 1,UUPv-Y EXP 3 WITHOUT PROPELLER
HARMONIC ANALYSES OF LONGITUDINAL VrLOCITY COMPONENT RATIOS fVX, V)
HARMONIC 9 10 11 12 1 14 15 16
RADIUS .456
AMPLITUDE .0022 .0023 .01.j 0014 .0013 .0007 .001.; .0017
PHASE ANGLE 7.7 96.7 1,30.4 I "8 7 182.0 249.0 30.4 i03.3
RADIUS = .633AMPLITUDE .0082 .00.36 .002 i .o9.' .001Il .0018 .001", .0005PHASE ANGLE = 9.8 88.1 1112.5, :'P1 1 50.4 143.8 20.' 290.8
RADIUS = .781AMPLITUDE .0141 .0120 .vo,.i .O '0 .003 .0078 .00OY .00,10
PHASE ANGLE 8.2 88.3 l1I4.2 7.1 6 6.1 85.5 167.1 261.5
RADIUS = .963AMPLITUDE .0115 .0124 .0(, .00 7 .0047 .0055 .0051 .0015
PHASE ANGLE 31.8 93.3 112.5 2,o .9 24.1 105.8 16!.2 232. -
RADIUS = .312
A'.7PLITUDE .0021 .0032 .005 7 0 13 .0030 .0049 •00-.1 .0O211
PHASE ANGLE = 205.8 104.8 142.9 I,3.4 32f.7 40.8 75.2 1d.0 ii.RADIUS = .417AMPLITUDE .0010 .0022 ,00Pl .0019 .0009 .00(3 001"1 .0010
PHASE ANGLE 359.6 100.4 11.9 1 1 20(.- 3 5..8 ,19.3 111.t
RADIUS = .583
AMPLITUDE = .0064 .00' .O1 4 .o I I '0 .010 .0015 .000'
.0004
P'!ASE ANGLE 10.1 86.9 II,.40 27.6 i:O.4
1j4.7 236.1 0,1.5
RADIUS c .750AI;,LI TUDE .0135 .0111 .ooC .0 I .0975 .0071 .o.,o .001,
CHASE ANGLE .2 88.0 1;b. ; 2 . 6 (.2 86.2 I6'1 . 262.7
RA)IJS - .917
ArbL LITUDE .0129 .0131 .00,10 00 I . COu" .0071 • 0. .00"7
P14ASE ANGLE , 21.4 .91.3 172.J 277 0 13.0 93.9 162.4 251.2
RADIUS = 1.083AMPLITUDE .0115 .0124 .00i( -.OC 17 .0017 .0055 .0051 .001'
PHASE ANGLE 31.8 93.3 112.5 01 0.8 24.1 105.8 161.2 232.6
62
TABLE A-6
HARMONIC ANALYSES OF ANGENTIAL VELOCITY COMPONENT RATIOSAT THE EXPERIMENTAL AND INTERPOLATED RADII OF THE TRANSVERSEWAKE SURVEY WITHOUT AN OPERATING PROPELLER
HARMONIC 1 2 3 4 5 6 7 8
RADIUS = .456AMPLIT TDE = .1472 .0202 .0186 .0100 .0065 .0078 .0057 .0018PHASE ANGLE 182.4 108.9 14 .2 353.7 25.9 33,3 28.7 69.5
RADIUS = .633AMPLITUDE .1755 .0108 .0116 .01 16 .0077 .0019 .003) .00,12PHASE ANGLE 2 177.8 127.4 3.9 354.7 1.2 29.9 21.8 22.9
RADIUS = .781AMPLITUDE 2 .1701 .0029 .0175 .01.1 .0053 .0036 .0036 .0015PHASE ANGLE z 181.7 12.5 10.8 357.9 ).5 30.0 59.7 28.8
RADIUS = .963AMPLITUDE 8 .1432 .0248 .0272 .0'56 .0085 .0036 .0055 .0023PHASE ANGLE x 194.3 342.1 351.8 343.5 332.0 272.9 267.9 288.3
RADIUS = .312AMPLITUDE .1034 .021J6 .0.3q1 .00,8 .0080 .0139 .O008 .0072PHASE ANGLE * 201.5 84.8 21.1 356.3 85.6 34.§ 49.0 173.4
RADIUS = .417
AMPLITUDE 2 .1364 .0221 .0223 .0098 .0062 .0092 .0063 .0018PHASE ANGLE 2 185.4 102.7 16.6 354.1 39.7 33.8 33.9 123.9
RADIUS = .583AMPLITUDE a .1713 .0139 .0120 .01'0 .0077 .0046 .0043 .00'11PHASE ANGLE z 178.0 124.3 5.3 354.0 3.8 30.9 19.b 25.8
RADIUS = .750AMPLITUDE = .1726 .0022 ,0162 .01 7 .COb6 .0040 .0041 .0020
L PHASE ANGLE = 180.5 82.7 12.0 3t.4.5 12.1 32.3 57.3 31.1
,,RADIUS = .917
AMPLITUDE .,1515 .0183 .02,12 •0 IL2 .0068 .0021 .0022 .0014PHASE ANGLE = 189.9 341.8 357.6 34m.8 341.7 306.1 277.9 295.3
RADIUS = 1.083AMPLITUDE 2 .1"d32 .0248 .0272 .0116 .0065 .0036 .0055 .0023PHASE ANGLE x 194.3 342.1 311.8 343.5 332.0 272.9 267.9 288.3
.1
63 - .63
TABLE A-6 CONTINUEDMODEL 5366 TRANSVERSE: EARI UVLY EXP 3 WITHOUT PROPELLER
HARMONIC ANALYSES OF TANGENTIAL vctOcI rY COMPONENT RATIOS JVT/V)
HARMONIC 9 10 11 12 13 14 15 16
RADIUS = .456AMPLITUDE .0034 .0024 .00 I, .3 o 4 .0014 .0008 .0010 .0009PHASE ANGLE 112.6 117.9 lo2. 1q ,7.3 157.9 138.2 121.1. 152 '
RADIUS = .633AMPLITUDE = .006 .0030 .020 .O06 .0020 .0015 .001, .0007PHASE ANGLE 70.2 38.5 .,5. 115.1 116.1 126.4 151.1 165.2
RADIUS = .781AMPLITUDE ..5 .0016 .0005 .005 C019 .0012 .0012 .0018PHASE ANGLE 162.6 25.0 8 7.7 a'; 8 f12.4 65.5 188.2 (5.9
RADIUS = .963AMP .ITUDE .0037 .0017 .- 01 Q4 . 5 .003b .0017 .002 ! 00:15PHASE ANGLE 254.0 137.6 110.4 1.:2 0 127. 1 151.6 134.J 135.5
RADIUS = .312AMPLITUDE z .0079 .0079 0p-,0 .ouj6 .0024 .0015 .000" .003PHASE ANGLE = 142.6 169.6 107.9 1b1.7 222.8 329.0 10.1 33.5
RADIUS = .417AMPLITUDE .0043 .0033 .0020 .009 .0014 .0003 .0007 .0010PHASE ANGLE 123.3 141.8 126.1 19,3 0 78.5 132.6 fO0.0 128 8
RADIUS = .583
AMPLITUDE .0020 .0028 .0021 .0015 .0019 .0015 .001,' .OC ' 9PHASE ANGLE 75.7 47.9 (30.6 148 5 1 '.4 132.6 144.2 178."
RADIUS = .750AMPLITUDE .0015 .0019 .0 0C, o.13 . 01 8 .0012 .001.) .001L,PHASE ANGLE 145.2 25.2 1 ;7 111.2 69.2 187.7 64.1
V RADIUS = .917A?; PLITUDE .0027 .0009 .0023 .OO12 .O02q .0011 .00, .00)0PHASE ANGLE 237.7 116.0 1"12.1 1;', 8 123.6 124.9 148.,4 110.0
RADIUS = 1 083At,PL I TUDE .0037 .0017 .,,03,l .C0 ,5 .0036 .0017 -002,3 .00.5PHASE ANGLE 254.0 137.6 130. 1 I', 0 127.1 151.6 134.J 135,5
64
I
APPENDIX B -
VELOCITY COMPONENT RATIOS AND HARMONIC ANALYSIS OF THE ROTATIONALWAKE SURVEY
i
65
I.<
0
t 0 3 . .....
-q I
-3'7 -- ,'3 ' 3 ', s
I'lt, E 'N CR G ,EE: S
Figure B-1 Velocity Component Ratios for Model 5366 from the Rotational
Wake Survey at the Propeller Rake Location for the 0.456 R~adius
66
-3~ -- - 4494------------------------------------------------------ - - - - - -- - - - - - - - - - - - - - - - - - - - - -
L.. ++_+ +...... . -...-.... +... .... .. + +.... .
,.+ - , . .,:c, ++ .- .- , -. . .-:+,. ,-" ++ 44" N , .W -.. .............. -,
~. ... ...... ...... ....... iI 0
N I - -
---------------------------------------------------- _
Figure B-2 -Velocity Component Ratios for Model 5366 from the Rotational
Wake Survey at the Propeller Rake Location for the 0.633 Radius
67
TwI-T. 7M -- P N
11 4 M 1444 1 q ~* *** -.. I*
I- I,
0 -'
F I
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Wake~ l Suvya''4PoelrRk Lcto o he071Rdu
IVV
_t I_ -___ _ _ I, .. __ _ - _ _ -.i
_____ _ ------- - - ----- - - -
I , I
'~ 2Z hC. ,NrC ! TN 5E rEL 5
~Figure R-3 - Velocity Component Ratios for Model 5366 from the Rotational
68
V. 7-W
ANCI~~ C N$EGR
Figure B-4 -Velocity Lomponent Ratiols for Mobdel 5366 from the Rotational; r Wake Survey at the Propeller Rake Location for the 0.963 Radius
69
1.2 •- . - 'j ~ .M I .I.
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0
,-. Q,,;.< ;
11
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- o -- - --- 1- H"--..-. i -* --- i
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Figure B-6 - Radial Distribution of the Mean Advance Angle and AdvanceAngle Variations from the Rotational Wake Survey at tb,,
Propeller Rake Location
71
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T~~~~~~~~ cr .1M c I '.X/ - L 0 1 c 1 : J r 0 t
DAVID W. TAYLOR NAVAL SHIP RESEARCH ANNAPOLIS LABORATORY
AND DEVELOPMENT CENTER ANNAPOLIS, ORD 21402
CARDEROCK LABORATORYHEADQUARTERS BETHESDA, MD 20084
00BETHESDA, MARYLAND 20084 IN REPLY REFER TO:
1524 :RBH
21 July 1980
From: Commander, David W. Taylor Naval Ship R&D Center
To: Distribution List
Subj: Forwarding of Technical Report
Ref: (a) Conference at DTNSRDC between NAVSEA (05R) and DTNSRDC (Code 154)on 14 Jul 1977
(b) DTNSRDC ltr 1524:WMB:svc/9245 dtd 22 Jul 1977
Encl: (1) DTNSRDC Ship Performance Department Report DTNSRDC/SPD-0833-02entitled, "Analysis of Wake Survey and Boundary Layer Measurementsfor the R/V ATHENA Represented by Model 5366 in the Anechoic WindTunnel," by R. Hurwitz and D. Jenkins (July 1980)
1. The results of the model boundary layer and wake survey experiments for theR/V ATHENA are forwarded herewith as enclosure (1) for your information and
retention as requested in references (a) and (b).
R. J. STENSONActing Head,Ship Powering Division
-AAIl f
g ,-
1524:RBH
21 July 1980 %
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I ',
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i
I}
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