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Copy No. 265 I

L CONFIDEN'IlIAL _ f",LlJj RM No. L6J14

NACA

RESEARCH MEMORANDUM CL1l.~S.L~·lC l'~vd L;A,!l;.!.uLt.U

BY AUTHOdITY J. w. Ck07LEY CL. GE ,1576 DATE 12-1-53 T.C.F.

DRAG MEASUREMENTS OF SYMMETRICAL CIRCULAR-ARCAND NICA 65-009

RECTANGULAR AIRFOILS HAVING AN ASPECT RATIO OF 2.7 AS

DETERMINED BY FLIGHT TESTS AT SUPERSONIC SP EEDS

By ,S DOCUM[NT ON LO ..., FROM HIE FILES OF

Sidney R. Alexander

L~gl~y~MB%rial Aeronautical Laboratory N nON'I A VI "I;'V no,' tAN 'f.. ~ If\. T I I

LA~ L ~" • 'I 0 , IA Langley Field, Va.

__ ..1 . 'f: , - - - - -

CLASSIFIED DOCUMENT

This docwnPllt contains clusllied 1nfQrmaUon atfecUng the National Defense of the UnIted State. withlJ'\ the meanln&: of the Espionage Act,

M I I UI't ) .. H tJ"" L~ BE AD DRESSE~e~~~l of~UI ~ont~:s tr::;l;=e;~ot: unauthorized person 1. prohibited by law . lnformaUon ao claaa1tled may be Imparted

only to perSOftS in tM mWtary aM naval aervicea of the UnJted State., appropriate ctv1l1an oftlceu aDJ employees of the Pederal

NATIONAL ADV'SORY COMMllTE~ FO Go"...",en' who bav. 0 I..,Umo" IDler .. ,

512 U ST " R AEI?OIllAUTlc.",,·r.ln . ..., to Unlu.d State. elU .. "" of known ... Rf t-l, N. W. loyally &lid dla:reUon wbo of neeesally muM. be

ASHINGTON 25, 0 Co lnIormed thereof.

NATIONAL ADVISORY COMMlffiE FOR AERONAUTICS

WASHINGTON

March 7, 1947

CONFIDENTIAL

https://ntrs.nasa.gov/search.jsp?R=19930085720 2018-12-01T11:59:18+00:00Z

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NACA EM No. L6J14 CONFIDENTIAL

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

RESEARCH MEMORANDUM ---------

RECTj\'~(GU'!~ AIFFOIIB HAVING AN ASPECT RATIO OF 2 . 7 AS

DJ;'c':'Em,fLNED BY FLIGHT TESTS Kr SUPERSONIC SPEEDS

By Si~~ey R· Alexander

SUMi'·MRY

]'light tests :have "beon conducted at supersonic speeds to determine the a.:r.ag c:l3,!'acteristics at zero lift of a wing having 8.

ci}:'cula:;'~"arc airfoil section vii th a maximum thiclmess of 9 percent ch0r·i'~. The wing pla.YJ. form iias rectangular and had an aspect ratio of 2.7. Inc11.1d.ec. for COL1I.a~:'ison a:::-e results of similar tests p:,:,e7iously conducted. on an !II-'I,CA 65 -009 airfoil . For the Mac:h number !'a::1S8 in78stig2.ted (0,05 . to 1.22), the NACA 65 ·009 airfoil prod.uced ::-Y.-T3t' values of li:;:'ag coefficient than the circular 'arc airfoil . T::1G differen'Je in arag coefficients of the t -wo airfoils was greatest at l1a.ch mr.foers nee.r 1 .0.

INTRODUCTIon

The possibilHy of practical flight at superGonic speeds has l o(i to the study of airfoil shapes that differ basically in profile from conventional n )lmd."'noso tYIles. Compa2'isons of the character­istics of rouno.-noRo and Cllill'p'''nose airfoil sections at sU0sonic and supersonic sp'3eds, J~espect ively, have been roportod in rofor­e~ces 1 aDd 2. No thooretical data and only extremely meager eXl'flrjmental data O!1 this ge neral subject, hm'70ve:c , are available for t"r.e tra:-lson.i.C speecl ra.!lge (the region of mixod flow). Tests hava thorefore been eonc.ucted at the test station of the Langley Pilotless Aircraft Rasoarch Division f!.t Wallops Island, Va., to doterrr.ine th'J zero-·lift drag ef a l~ectangular , 9-pcrcent d.rcular­arc a.irfoil of U3pect ratio 2 . '7 mounted on c. reel~et-pro:pellod body. r::'hi.3 valuo of BRpeei'. ratio is 'based on the total idng Spal1. and a':'ea i:r:,'.)ludtr~g tho part 6(lClosed by the body. For comparj.son, the results of tests of t.he rect::mgular nASA 65-009 airfoil, which hns tho same aspoct ratio} presented. in reforence 3 are included.

CO.li'FIDENTIAL

2 C') NFIDEN'I'IAL NACA PM No. L6J:~

BODY AID TESTS

A photog:c'all:.t of the test ood.y is shown as fisure 1. T'.ae "body was apprcxir!.'9.tcJ.y 5 feat long and 5 inches in diaJ~ete:r and. ·i.1':18 of wooden cons tn;..c t,;, on , ')":'he 9-percent circ·'J.la~'-arc airfoil) of :::'5-':'3-inch span, was TIlO1)r.'0cci (·n the 1:·c..cy so as to have the quart8r--0hO-rd p0iIlt at the same lon.sit'l~d.inal stClti.)n a.s t~e d8sign centf'r' of gL'avjt.y . ':".he air foH hall nei i2!G!:' tapt'lr, t;..ric'G,. nor dihedral . Tht'l lea-:;.ing and

1 tx·a.iling 8Qg6S \[81'''' .!:oL1Il(l'3a. off to a ;4-inch rao,i:..ls ,,-!licn was

c.;

a:.Ol,;,t 30 percent of t~'lG 19I1.d.ing-edge radius of 'the NACA 65-s8ries ai:cfoil section. :8.··.cept for a id'cl l sec tio:J., the test bony i.,i ton the 0ircul.ar -a.:::'C a1.:'foil and !:oL.e c')mparable test 'boa.y wj.-th the !,'{,\CA -S5 -009 airfoil l'i' ::efe:;:'ence 3 were ali~e . A cUillpa:cison of the a::..rfoil s'.?c"viorlS i~lve5tiga +:.ed. i8 :pres ell ted in figu,,:,e 2, Al thC1J.g!1 tx;e Cl)nl"E'n'Gil)::16.1 oe:; SiO:l hFl.S a rO';l!lded r:.ose, the 8101)e of tr.6 s\~rfaee 0: the fro~'lc pa.:'t of \,f.e a:l.:::foil is ;-I\.ucr~ ffiore gradual and 't.z18 rear pa:.'t is :l1'J.ch fl':l8 than fc:t' "',:09 .:':,'c·c..le:c -c,re ai:!.'foil . Two '1l.octels o=: eacl'l c.;)migLLrat10n wero fired unde;,' sj ;:;:iJ.a:;,~ a t::n08:pheri c cO:J.ditions .

All the test, "ucd.ies ',;e-::e pr o:pelled 'by 3.25"i-:'lch-d.iar..1etel~ Mk. 7 a:" rcra.ft rocket j:'0tOX'S enc],,')sed -,.,i til:..n the bodies . A:' a r-reig;:j ::;io:1. t.e!1J.l'eratu):'e of 69(1 p) the r .)cket i!lotor provides about 2200 l;ounc..s o:f t'~nst :'or a:;;>proximately O. 8i' sac o:!:"_d .

'.Elle test '!J~l(li AS} as Wt:lJ.l a.s the tes t bodi es of reference 3) we":'o 12.unche:5. at a1':, ele7Fl.tion a:l8J,e of 750 to the horlzontal. :aecaU9'3 o-f t~:E) ~!ig:tl eJ.e-.ratj.C'71 a:-'<51e 8l.,i tbe short duration of bUI'r..tng of t:'Je .::'o:;ket l!.lotOl'; ~,he t:;: Jectory of the bodies during their 8upe':-:sC'Ej,c c.oasttr!8 flig~.t ,: n'tt3l' t.he l'i..~ol;ellan. t T~'as expendet!) ,:as Cl.?prOXlna t.e ly a str.'llg::'1t l::':-.e. ~rj'e fl:iG'"~ velocity was measU1'ed al1ri:1 t,h1s coe.stiIl.g rl:O:':1ocl 'by raea::.18 of C'< ,-:;\-1 D'J:fr)ler raQur set (A...IIJ/T.fS-5) :l.00.:t.tec, at the po=-::-~'0 of lauClclline. ':,'i'.e values of t.emperature and sta'Cic preSf:i ..... ..:.ne 1J.:Jea. in cu.lcula·\~ing d:..'ag coefficients and Mach number 'were o"b'talned fJ'o;n rac..10son~~e obe3rva ticns ::na.de at the time of firir:.g.

RES'L"LTS A:VD DISCUSSION

':.'he variation of velocity with flight time fer on of the c1~,'L;ulal' -arc aiL·foilllJ.odels, as measured with the radar unit, is •. :cesented in fi re 3 .. Tne pa:rt of the veloci t y Cl1:~ 'y e correspondi:n , to the Urne dl.'.2' :i r:.g iillic;h coaGting flight was attained. ('after the eEd. 0: ·bu .. r:1ing) vas gra:9"licc~'::'ly Ql.fferentia ted to obtain the decele:!"'.-3. tion,

C01'FIDENTIAl,

com'IDENTlAL

The values t1:,us obtai ned a r e presen ted i n figttre 4 as a function OI~ the f.ligU, velocity for tHO identical tes t bo.:ti e s vilt~ circu.la r­DYC a iri'oils. Since tl1eS9 mociels 'tlere fired under identical a'Lmos,pheric conJi ~:ons . tno r1i.ffer-~nce between the C~E-'Ves can De partly at.tl'j"butpd. to the wClg11t differenco betweon the t-/i'O ~odels .

3

Fro!:'! tee cur'Yes of fj £12r e 4} the tota l drag tas i)een COc'!)'c~ted

and is pr8sen te,~. in figure :5 :plotted agaulSt :Mach IlUT£l3JC~: . \tli t'::l +,:18 ,tn:.:-del 'fieig!lt :;Oi TJ:'JW ll into account , t he va riation of c,rag wi tCl ).ach j~'H.',DeX' shou] d be '':.he same; and conse quently one cu~:'Ve ;,-a.s fair;)(). t.r.t:'o"tlgh i.,:·~e r esul t.o of' bo~b -tests , the avorage Boattl-):;:' of t l'J.8

G9.lculat ed. POill'::.S f::c\'D. t::JC fa.ired line being aPJ/'coxl~tely ±3 peroent . Drag coe:ft".cien'-':'s ,:-~_(:",l1t),t6d f rom the d.at a of figu.~~ e 5 an~. ba€'!ed. on an eXI'cse,: ',.1i:,,:g area o·~ 2~,O 81"Ja:;:'fJ inciles a r e presen te.} in ::'i g')re 6 (a ) • T:,'),e ('(jrT'espcnCl.i·.l~ C't.L""-3S fOl' t,he test b ody w'i th t ho NACA (5 ·-oC,,;) a i'i" ­foj 1 ECd. for' arl ide;:-,~ ·, ic.D.l tS8 t ody vri thont 'wings ar'e Llc: lu,1ed ::O:i.'

v'.")!.'llpariso::1,. :8'::8' l1'8 (;(a) 811m. s tlLa t, fOl' J,1£i.cl'l, r..uml)o~s bet'ween 0.85 a:lrl J.. 2~) the ".;OU:, -,.;i th tlle N,:.CA h5 -009 1"ing p:o.'od:lc8'1 lCJwer vnlues of total C?B c08ff:J,ciont l~1A.:1, 11:;.J. t he bo:ly 'N'ith tho c i ;.:-cular -a rc 'Io,-ing. Genarall: T Siictj.[ '. :r.esu.l ts have 'been obta ined r esent ,ly ~y t il') Lanc31ey ~" ::"lg:r.t l ~8SeaY'(!h :Uivisio:l. using f r eely '-falline-body teclmiq,LlG . The greatest d:;.ffer 8nce 'bet·"eer.. t he irD.gs of the t\.;o 'il:'.ng8 can be see"\" to OCCU:i.~ .:leer a Ma ch :mDi~er of 1 .0. CO;X'8spondi:-:g em-ves or W1Qg (teE.S coefficient) dK~ived by taking t:c.e d.iffe:r enc-s bO'C'yTeeD tbe 'JiH~ge r:;, a::-~,i vTing.l.es s b ac.ies of figure 6 (a )) are p-:esented iYl i'tg.J.!'8 6 (0) . '~[:8 va] ne.a of ~"'ing drag coeffiCient 0.e tel"IDi:l.d(i 'by thi s !'let:!lOd 11J.\~ 11~Ue 'vling -fuselage - inte:cfer ence effe.::: ts . InformD,'tion c,)n ~;fl;'ning the 7o:rlO-t.inn cf t~1e drag -coeffi cient cu:;,nves of tr.e l-[A',:A 65 -009 anC'. tl"fl o;;:m,etr::Lcal circular-arc a i rfotls beyo:ud the testE.d Moch n'v:;:i;)p.y --';.:;:rlGc C0111d. be ec;ttiblisne(!. only by fUj"-:;h er ij,l. -

ves tiga :Jion D.. -t r. ::'ghG~~ sj!8olio .

CONCLUDING RE.t\1ARKS

'1.'h8 r esuJ.ts of supercon ic flight t ests to determine th9 drag of a l~ectangulaY') 9 -;>ol'cent c ir'cul a r -a:::'c o.j rfoil of as:pec t rt.: t i c 2 ·7 illounted on a rockeT. -P::o: 'ollf311ed b ody are present ed. The d,2.'ag coeff'lcients of a siL<lilar tesc, ~)c\::y vi th 8...'1 rACA 65 --009 airfoil ob SO-ined in the sc:n.e ICEumer have also been inch~d.ed for c om.pari son. ]!'or Iv'.ach ni:G"D.be~~s

'betveen 0 . 85 D.ni 1 . 22) the values of drag coe ffic iont of the l~AC_"- 65-009 c.:.L:foil were lower than t hose produced 'by the circul:!,r -

CONFIDENTI AL

4 NACA RM No. L6Jli+

arc ail~f()il . ':::hA d iffe.r'ence in drag eoeffieJents of the two air foils WE'. S greatest !lear a Iv'Ja Jh number of 1 .0 .

Langley Memo:'ial Ae~('o.na.utieal Laboratory National ]'.,:"rjSJJ'Y Com:Illttee for Aeronautics

Langley !i'ield, 'fa .

REJi'ruiENCES

1 . Lindsey J W. :t!'.) Daley J e:rnard H. , and Hut:l.phreys , Nil ton l', : The Flew· and Force C':!.i:i:;,'ae teristtes of Supel'sonte Airfoils a t Jhgh SLi~sonic Speeds . HACA TN No. 1211, 191~7.

2 . Bus~iIlannJ A . ) l'lY),d Halcb_ e1' , 0 .: Profileigenschaf·Len bei Uberse~1alJ.geschwindi8kEd t , Forsch. auf dem Ge'b . des Ingenieu:.:"',T.> Ausg . b., Bd. 4, Heft 2 , March/April 1933, :pp . 7-92.

3 . Alexand.er, Siir..ey R.) and Katz, Ellis ; Drag Characteristics of Rectarl{];i,llar a...'1d s,olupt-Back NACi'. 65 -009 Airfoils Hav1.ng Aspect Hatio3 of 1.5 a nd 2 .7 as Determined 1)y FliGht Tests at Supet SC'H C Speeds. NACA RM No . L6j·16> 1946 .

CONFIDENTIAL

NACA RM No. L6Jl4 CONFIDENTIAL

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Fig. 1

Figure 1. - General arrangement of test body with 9-percent circular­arc airfoil with an aspect ratio of 2.7 .

CONFIDENTIAL

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NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

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CONFIDENTIAL

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COMMITTEE FOR AERONAUTICS

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CONFIDENT I AL

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CONFIDE NTIAL

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NATIONAL ADVISORY

COMMITTEE fOR AERONAUTICS

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