Document
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NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS ORIGINALLY ISSUED November 1945 as Advance Confldentl81 Report L5010 EFFECTS OF COMPRESSnHLITY ON TlIE MAX.DruM IJFr CHARACTERISTICS AND SPANWISE LOAD DISTR:muI'ION OF A 12-FOOT-SPAN FIGHTER-TYPE WING OF NACA 230-sERIES AIRFOIL SECTIONS By E. o. Pearson, Jr., A. J. Evans and F. E. West, Jr.
LBIlgley Memorial Aeronautical. Laboratory LBIlgley Field, Va.
WASHINGTON NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were pre- vi ously held under a security status but are now unclassified. Some of these reports were not tech- nically edited. All have been reproduced without change in order to expedite general distribution .
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ijAC A ACR 10 . L5G I O I ,T ATIONA L AD VISORv CO~'F 'UT T E E FOR AERO:J ALTT I C') ADVANC E CONFIDE'.JTIA L REPORT r CHARJ..C .rERIS'J.'IC'3 AE D SPA NV :IS E L OA D DIS 'lR I BU':2IO T OF A 12 - POO T - SPAH PIGJ:'~E:,: - 'r YP:C V lI lTG OF "T h.CA 230 - SERISS AIR?OIL S:SCTIOHS By E . O. Pear80n , Jr . , A. J . Eva ns and F . E . v','e s t, Jr .
SU~.1';i-;.RY Force and pr es su re - distrfrution mca8~ r e~e~ts were made on a fi[ht e r - tT)e wing model of corv8ntlonal
J-Ji- _CA 230 - series b.= r·['''':l s'3c+:io'1s in che Lar:.~ley IE - foot
hi gh - speed t 1..'nnel to dete r.l i ::-~e the t3;:"ect8 of cor:~re8:::d b i l i t;Y' cn ":h6 rri,-,-yj.!:I1X'l lift cha .t 'Bc":6 i. iotics B.nd the S)2.n - wise load clistr~rutlor . Th nuge;).&' 2n,_le of attack 0 0 inve~ tifa~e~ W3.S fr:.n - 10 to 24: . ':2:be :.1.lc:t n'J.n:ter range Vias :.':'rom 0 . 20 to 0 . 70 at s:'.1all 8nG. ~l1eclilJ.": angle~ of attack and from 0 . 15 to 0 . 625 at very large ancles of attac~ .
In the f;1ac~ nU]11~ er r3.nfe from 0 . 15 to 0 . 55 , the maximum lift cfJeffic..i.ent first incre<:>sed 'lith increasing lvIaCD nv..o'T.ber a ni the?]. c.ecreo .s ed ra;;idly after havinE:, r 6achec. a .nea:-c VLIU3 c·t a :.Iacb n r-:,")6 ... ' of 0.:::'0 . 1.t 1.1a ch nu.'1o.;;rs "'l:LI ·r .. er th&r.. O. 5t , t r e ::>atc 01.' c .. e(;rpaEe or' ::na ·:i :r.llli11 lift coe:l'::'cient \' !ith I:S.C~1 nUo'T':)er- W·.lEl CO::1.fl::,c6_'ably ::"f. dU0 ed .
At theee h;fter epsedp t~e lift coefficient continued to inc ... 8G.se with 3.r1[,le of a:"G!?,C;~ well of'yond tr_e "nr le at whic~"' . r.-:ar~cec flo1!! s'Jparation or ~tallinr: occur:"Ed , nne.
th e ~.a:xir1Ur.1 li ft coe.:·ficicnt '"as r-each:.d b.t ancles 10° to 12 be·.;ond -ete stallin ,=: a nc;le .
N si[nificant chanses in tle span lo~d distriou ion were founrl to 0ccur ~e low the stall nt any of the t0s t sp eecs . '::l1en t' E. wL C E'tallEd ro .t ~igh SD(;ec..s , tl .... e res ultc.:.nt l oad unde:;:l\!E.nt a model'ate outboard slift , wh! ch res ulte8, in i ncreas6f:l in root bend i r..c:; r.o'iert up to about 10 p(; rce nt .
----- -- -----~- -- ~ ---- ---- ~ 2 CONPI D :B.'NT I!1.L HACA ACR No . L5G10 J l~T]'ODL'CT I 02:- ~ind - tunnel te~ts sf a rectan[ular winp of NASA 0012 airfoil sec ti on (referenc '3 1) sbovred that the '11a~~i:mUlil 1 i f t Y
coe::flci ent reached a r ea:{ value at the loVJ Ma811 nU ;1;)Or of
0 . 1 9 J.nc. decrea.:'ed rClT'idly as t _ 1e Nidch nu:no€r 1': was
increclred from tri S v2_lv_e up to the :lighest Mach nwnber of t:le tests 0.1 ~ 0 . 35 ) . Although these te~tf.l were necessarily limited in scope , they in~ic3ted tho importanc e of a knowled£e of the effect of com1.)rcssibili ty on the maxll111..1..'1l lift coeffic~tent both in the est.i..l-:1ution of the maneuverins p-el' formal1ce and loads of high - s:r:;eed aircr8.ft and 3.11 the-- interp r ethtion of ';rind - tunnel may.imUlT. lift
data as a;:pl i ed. t o the -predi c tior:. 0-:: air;Jlene cr-aracter -
istics a t low speeds .
r.: "' 1"8 r e c ent bvo - di.nensi l"1 .::la l . wind - tunnel tests of a nu,'1lber of propel l er - type .ai rfJils ovor a relat:i.vely large 1'ach nu_ ~')e_ r r anfe ( referen c e -2 ) <:!hoVv'bd effec t.,. for the thicl:er ai rf oils s:U:1i l ar __ to those I). i' reference 1 and in addi t i on . .sh o wed l arGe i nc_rease:::. in -the m <: ,ximum lift coef - ficien t s ta rt .ing at I:lach nu:n'o8rs of about G. 5 . FliGht tests of fi~hter airplane~ r e~orted in references 3 and 4 s'loi!Jed la r ge d6c r ea-ses in t he lift ~ effic i ent c rre - sponc:'inr t o t he stall -u p to !ract. numbers of about 0 . 6 .
A hig-h - speed wind - tu n:18 l imr6f:t i gation of a number of thr e e - di~8~8ional win~s of different ai rf oi l secti ns haR been undertdken to provide nore detai l ed inf r~ation on the hirh - soeed stalling phen o mena . Uearurements to dete r mi ne the effe c t r") f compre::osibiJ i ty on the spanvris e load diat r ibution we r e in c luded i ~ the proeralli becuuse of t he related il"J.portan c e of the l oad distribut i on a . '3 a deterrn " ning f~ctor of the stren[th requirements of winss .
T~1e present report Gi v e s the preliminary reS-LIlts of force and p r e<:!sure Measurements in the Lane:ley 16 - foo t high - speed t unnel 'JD the first of a serie s of v: ing8 . T~_e mo~el t ested w~s a fighter - type wing hcving an a spec t ratio of 6 , a ta~er ratio of ~ : l , and conv e ntional ire _ 230 - series airfoil se c tions .
C0 Kf' I DE1~T I J.. L l~ ACA I.C R ~,ro . L .sC 1 0
v true airspee~ , feet )e1' second
a ~reed of ROllnd in air , feet fcr secoDd J.i1::.ch r:.u..y'oer (Vi a ) p [lir dene i ty , slues ])cr c u- .)ic foot q dJna~ic pressure , pounds )e r s~uure foo t
Reynolc.s nu~,bel ' ( i?'~' ~)
R , I"" coef f " cient of viscosity ~f air , ~lu~s rer foo - second Tne for c[c in ~ ry ~~ol s repre~e1t th e undis urbed strea m. va l ue3 .
cro2~ - ·~e~t~o~&1 b~ea o~ tje tu~ cl ~t t~e throat , C s I ~.C: r a :. c t D ~in~ ~rea , 8Quare feet b t pi"~ "1'1' ~'C' d-:':: t ~;.,,~ ,:. e "T. e" 2l- re '"1 f r o,., the p lc.r:.e n f y ::'.'Y.I_ctr:· , feet c rea'1 cf.,ord, fe 2 -;:; ( Sit ) Ghoro at l oca tior~ , f e et c drfo':'l r::C~:)-'l-L~ r'_j.cl~:-l3~.,:: 0:' t ir:'o::'l section corr'JfTonding t t) the ',(a.:-" c:::)r::l, fe::t
c O:~F ID-Sl~TI AL
4 C ONP IDEliT IAL N ACA ACR ~-Jo . L 5GIO L wi ng lift , r oun d s ,..
'.'1in 2: lift eoefficient (L_) v T ~ QSj . C- 8ct::"on '1 0rrrc al fo r Ge (.f:)r~e DeI' 'l'!:it ~~pan ), :po l'.nds n rer foot.
sec clon llol"r!"a l - forcf) C oefi. i cient c n c c lo ad coef f ici e nt
-
n C s b
/
\
I C /,. "2 C! .
,..
C C V-T win ,p: nor1"'& l - f o::.'c e r;o ef f ic i ent _ ':: I
r..c
dj
Sue s
~
cor rec~ed. an ,le of attal.:;T of tlle l' OCt sr3ction a (8 ec'S:} . ·:.n 'it t he rJ aYlE; of 8~J,P et~7 ), ':_eg re e s anrlc - of - [ tt8. c L C0r:"'ec t·i.CTI .]118 t o the jet [ ~ a.lL b01)'rL~t l'Y - ~ Y',G.1.'C e el. UP,1[[',Sr.. a.t the lift.LnG li ne ,
degree s ( 57 • ~ 6 ~ C" \)
\ v-w) "" .j.. ' a .L unc u lOr. o~ the T'c.tio cf wlnp S ;)8-1"1 to ttL..'inel ~ r~ b '. 4 /b ',8 .....
( lJ'l v
d.iameter + + . - I . .
+
'_)
\8 '1 6 \ D .: 64
oJ)
\D I \ L a an~le - of - at~ack corre~tlon ~ue t~ the jet 6. sc . bO'.l~}(~ ary - i nd 'J.C cd s t,j"efTroline C'lr\.·g. ::;ure , ! -.. d:':..8.E'-'8.1.T c.t.i(; skeL;('.h .of tl:e ~.':u·g :~loc.el uced 'in' the t e~t 9 Is fi~8n in ~ipure 1 . ~he ~_ · j~c i ~~ l d~~eDsi0n8 gi 'len i::1 lbe f>::-ure anJ '-ltLe ~: Y'eY't':"rlE,nt :;.D.for.",:c.\. t iQ.l-~ are f i~eL in the f0 11 0wing list : J ACA ACR No . L5GI0 C ONFIDE'T'I IAL Span , ft • A1.'ea , sq ft ARJ,lect roatitJ . 6 Toper ratio Geor:etl'ic o.-:d a.e:('od·,:,rnamic twist (v,rasn)ut), deg . 11" . 2 Ro,..., t section . ",-TACA 2.")0 1 6 Tip sectio11 0 •••••••• • c •• =\TAGA. 23009
~ihedral (ulong t~e 1/4 chord line) , ~eg . o
Sweepback (alon:.:': tl~e J_/4. c~ ord Ij.ne) , c;'eg 3 .1 8 The wing '. vas of bu i It - up steel c r)n:::tr'lC tion and vas Jl1.8.chined ill .suc h a marlrer tl1at sll.rf3.co e1ementf! cOTh'1ecting equal percentage - chord points of the root and tip sections we r e straiGht lines .
Th i rtv - tbree pre:8ure orific€3 were d!strlb~ted over each of s:: .. wiDe; "ect:':',)ns , tbe sr-·a.r.."rise locations of "iri ch G.re gi \ en in f lr:·L..Y>e : . 111 e ch:)y·f'.vi '36 01 stJ'ib'.lticn of Iress ITe orifices f~r a ty pica l section lQ als0 fhown in figure 1 . 'Its ~H'es"'ure tubes .lere orou~:1:; out of t~1e ':linG to :nulL ipJ.e - Ll.;')S 'an')~1etl3rS in the te...,t c' .ar be:.' by r:Jean s of t~e bOJm ~n1 ~ov~ble "trut arra~:emEnt Etown in f~g ure 2 . ieo r tho f.Jr',~e te::-Ls t:1.e t-o.)~ B!:l.':: :::trut ,,'ere re:moved and the r::OO!il repJ.':.cerl '·i th a s[',ort iairins , wtich 1 s sbown i1.1 f i,'nre 1 .
The ,':in:")· '!J&..<' rYl'lLted ct thG t·.lillJ.e1 Cf;nter l :" ne orc hielded ~t;rut~ ravin[ a thic,~nE:8s - r,hor·d ~'ati.) of 0 . 15 .
The thic "r.es2 - c"'1ord ratio of the sh-i_elds 1,. 8.3 0 . 124 . ~ i8 - J:i.re 3 i'} a p;..t· ... co.rrra;Jh. of +ho vl:'ng "'1011r,tcd 1...;-r-=-e1:t in the tU!:l.~el for the force teats .
::'-0<;": of t;re te~T, r1J2'"~S .. ere m&c.e ··d th t.l-:.0 .s.IY'2.P, of at~ack "le2.(- Gor:pt' nt \,;:lile tiJe tU'1:1el siJ.qed 1'1' S vD.Y'ied fr')r:! about 1;:,0 mil.e S De ' ..... rou!' to the --:n:<:·l P'.U'1'! Clpeed 1 '·n' . 'b1c. · ....... " 1.-. •. ~ r-~ ,.; r 'r-' co .p a.1..~n 1, . -·0 .• CO ),-,<.:.lr,Q. ,~V , ,JllC'd _0_ \._nt, a,. ~E:v 0_ L..L,aC O_L..V.~e_l a:-1d 4° VID..S &D ;roxL:lb.te1y [;20 Il'l:...les per tl,)l'r . ~he corre - spo:-.di 0' ;~b.C·~l l~1.:.r"~er ra~li e '''::,[, fry! 0 . 20 0 ') . '70, b.!':.d.
t:18 cor:-·e ;'~.JO:1(~: ng r'nn: e of' avcrc,fG hE-'r>·. lc.E' l1"Lbe:' v;a s 6 • frOT.l :3 . 0 x· lOC to f: . l x 10 l~lig'l.T'e ~1; sho'!f'3 t-Le varia - h tion of 2verJ.fE -;e;'1:01d.~ r-U:·'1 c·'" ·. litl " :acr- l1W,l er e ~or very 12~ce w~ng an~le3 ni attack ~hc ~aY~IQ~ obt3.iilnble
tunl'el e: Bed ,,·&s a·"'o1..~t 160 r1..':.}es .Jer· nour' , .":h:.ch corre -
s.:~or:.ds 1~G a ';<...ch nUP.lber cf a:x'u.t 0 . (,25 . III +:he deter - ~in~tion of ~&7i~'mi lift coc;ficients ad6itiJna1 tests ',vere ~.:ad6 'ifi:;h th·.; tun:Iel speE.d ~eld consta'1t while the angle of at tc:... c.l{ was varied In the rer;ion ne8 .r r:1aXirr.u..111 l if t. The P.:bOll,etl'ic 9.nr"le - of - attacl,: r<....l1t...re of the tests ~o 0 ~ was from - 10 t o 24 • 6 C OFF' I DEIJ? I ;' L NACA A~R No . L5G I O g In t~e load - rt: ~tr4bution test the stat~c preS8ures OV6r t:-lG six "!inl3: sec ti~r 9: .;.~8 i :l(J~ cated b7 88' eNtl m' 1 ti DIe - tu"IJe llian0r16 t'3r 0 : 1,"'31'e recnl ced p~o to€,"ra)',':'caP y .
rr~le c'!:10rc~'ivi ss proSs :'''urs (:i str::' "bl; t l."'ns cleterl'-lned fro111 tLe .... o r:)''':ot8, rf.q~'1::'c re::;"l2.'ds '''ere 'lLt:r:crated ~.;cc;:" .. 8n:tcally to ftnd tl-'9 <'cct:"'L nO~""Yilal - f'orce c..()ef~~('.iclt~ .
beGn co r recteG fo r al'd tu ... '1ne I - naIl The stru~ tare f~rces were Jet~r~ Ded from te~ts w::.th t~!.e "!lllr; inverted ':,:5.th ,<,:10. '.'Jt:-:..,uc ir:1a:.-e ~u~:)or t SC~~Ut8 . ~ ::~tal:;"ed . '; .P~..)toi;r8,.pn o~ t>::: irivc::;}.'t6d \'{j r.f.: ','Jith thIS iT1Ci.,~·e struts ~n:;La:,~,ed is ri'/er. i"1 n ,.CnI's O . '1 he largs st ] ncreT"'8ilt '3 of J. if t cae ff' i,e ':'er. t ('.ue to tIle snp~ool' t str\..~ts v'ere bctvLen O. 'J3 and. 0 . 04 .
The ef~ecti~e rnisalineuent a~rle of t~c air ctrcam
VI,"t3 de~8r):r'-~illF freI. teqts or the JlJ r1~"" tl!: l"ir~llt anc~ ir' .. "veJ.,te d
VIi th trle i1l'l8.ge struts irJ.sta L ,ed anc~ \":l.".l f0U21G. t.J 00 CO:1stan t at 0 . 1 5° tbr~u[bout t he speed r a~Lo of the te~ts .
Iil order to p2"e V ent air le8.l(c,.:"E: t'fH'8UC'1 U:.e st~'u t stields, thln rUJ'';0I' diart.racT"' s vlere fi tte':~ nr')LU'!.c:' tl'18 bas6 e of the stielde . A~ ~1Gjtia~[1 correct!c~ to the l ift ~a3 neccPfit&ted becau~e of a rres~ure fiffe~erti~ l a cress t}:e c1iaphracn-:'2 . This j~,re.3':llI'C dif'feI'l;ntial VJ8.13 mea8urcd ~urin~ the f0rce te~tf 07 Feans of a mi:ro - m&n:>meter , ancl a c~librc.ti0:1 1,;"8.S L(,,::e '."[ltl1 the Wi!l!.:' re~",ove ..... to d'3t8 r :O;l:tne t~1e v3.:-,latJ.on of lift. r"ree v':: th ~ressure ~iffere~tirl . This cor~6ction vas VEry ~~D ll in tr:e :;.'e[i'-)11 ot r~axiT"'.U'~l li:'t ( I e":" t.:'lan cne - :lalf' of 1 per e~ t at all spee~3 ) .
T~e effecte of t~q tun~el walls ~er6 acccunt0d fo r by the ~ethode of rE:'erences f , 6 , ard 7 aq fo l 1aws : T he principal part cf the an~le - o~ - attdck corrcct oD civen lD referEnce 5 is T" ·ie e qu8tion :1.f sTrictly v:J,J.ic' or:1y for- the case:f a n e l lipt~ca l apanwise loa~ tistl'i~uticn . A c~eck ~alculat i o n ~TACh. Ae~ ~b . LE:C-IO C Ol';-F IDi.l' 1'I..:..r 7 b~T a Y'10: e e:,~5.c t but . O::"E det&iled pr')cedur'8 t'aseci on ehe ex~_'erinFn!~ally dt:tel'~Tlir,ed S.JG.L 108c;in2; revealed tb",t t.he error l~cu~red by the use of the sj~Dle ~ for~. WdS Lezli - sible . At a winu lift coelficient of 1 . 0 the correction W8S 0 . 93° .
An ad~~~ionaJ correcti~n to t~e anrle of attack due to an ~nduced curvature of the flow was calculated fro~ the equ&tio~ 'l1J-lis e Clua tion is ba:::;ed or:. the o~"iginal i::-:.cO! .1!'l re. " :>ible - flow derivation of reference 6 . T~G M06ificat!0n
f1: 1.1 1 S .0 '1 ven in refe:!:"Gnr;e s . '=.':12.. s correc t5 on
arnou~tcd to 0:16 at a lift c0efric~ent 0: 1 . 0 an~ a ]i:a(?h nt;;."'ber of 'J . 6 .
Cor-rectionp to :'~(. strsam vclocity , dyna"!lic pressure , r aDd l\;acn nUY','uer, a1::1 T:.O t:16 v:tn J ift co 0 ~ ~':i c- i en t (',ue to consb'i c t:~or. efrec t s "ere .::al c ulated [1:- the .,.tle th0d of referer.ce 7 . ';lhe c,")r:-cectlo~ to tLe vr-locl ty is 6.'1 _
,)here i:,V is t: e efi'€ctiv'3 iLc:!:"(;r1'?ntL:.l v.-::l city du-? to
c~nstr-ict~on , D a~d H ~re the ~r-adt~ and heicht of a rectar!I' "lla r tULDel, ar10 eDo is the wlnc; profile - drag coeffIcient. lhe two terms on tte ~i,~t o~ the equatIon c-ive tl:e VE..locity incre "!1en ts due , Y'.;}C',tJect5 rely, t:) II s0 1ier' ll cons~rictiu:l and "1Ia:,:e ~:)nstrlcti:)no SLice L,e ~a:-:;nitude of t:1e wq~ce CO:1S tric tieD effec t i,: a func tieD of tho veloci ty 108s L: t'1f' v'a::8 E,"1r tre siz6 .,i t':::e "[:{e , tre rorrecticm :,P ej{1':'8~sec in tE:, 'TIC; of tl')~ n~of:ll::> - r:rag ('oef_'~ cis'1t, '.';::~ich ic- a2.se a 1".mctjon of t1r)SC '1u8.r.tit_:.c~ .
~',o J c ',leoretical treatment of t-,1e pro 'lel~ 8:' c)l1stric - ti'J::1 effe "tr f'J1" 8. fi.ci:o ':'j r:~ ::":-1 a. clrc'11[lr t,lm:.el ~;:i·s ts a t the pTe p en t ti me J ay':' L1E rf"n'ego:l.n[ r<3l-'-'t i ')n ':8 c: Lourht to represent :ho bent a va!lable arp~oyirr~~~on . As m)~ified for the care 'Jf the ~ircular ~'ll~:el , the e1uati~n becaffie :.;v _ '.Jh(;re H in this c&se is t'1.C ';;.-TP:"2SG : :oiL"ht of -':,};G t"_:~:-:e l ill the re[,ion o'::c':.pieG. by the v,i'l.e; . 'Il~le ,:;ollstJ-'ictio ' ,_ c.Ol'rec tions to the C.Y:l.[l:r.;ic j.'l'e s S J.r€ , ' ,rd.C~] !"luI,be::-' (refer' - , e1'"~(;e 3) , &n1j vlin -- lift coef.tJ.cie~lt are CI.S fC'~.lo\'Vc; : r - V G~ jG -- ".T" ~ :f
(, ,~)
L4 l~': :...V
:', r-~ .. ;1'-' ..i... .... , 0 .: ..
. - + ,I '1 I \ .\ ., - u:JL '
= .=:-q
( :~~_I q tL .. e CJ1l.:~~'~ '~r crl 11~~:~~.J€r· l'2.r_[.(c.
~\t d. ~~eO~le tI~=-c Cirl .. :le 0':: a tac.'~ 21.r :~o 0..:("(1 G. ;·.'~9.0:-2 nu': .... t:--r o.J~ (' . 7 tr~c corrE:C t~_on. '3 to the li:Ct c:)o:Lli0ie:r1t :~!lC .. !~!~·~·:~.l;. ~'J.':"''-bC:· l'er'e , re2;J3ctivel:r , lQ C: :JC1'cent z..nc~. r! . G l_,e.1."cent . A.~ cL .. 2:18s 01" a~tCJ.C; - ~ d ·:)v~.:;.
"C~'le Gtal J. ~~r~1f;re ~J~6 dr&p~ bec,?!·.p' "7;" :~ry 13. 1 'r " e (.inr:1J~ .~i:~ "T\Te o.f " l:J~r!"r' .,.~r.·{n ) . be COT'ytt' r- t'~()f1 \ -' r nr · "......, · Ct.7' "r...~~e -Ir.~no ...,tr-:-r)('t' U _ .J'f)'; \ . C~i .. oJ , 1.1 _. ._ - ... ... 1.. ..... :. .... ~t·~ · t .:. ..... ~ ...... .1..1 _ •.• ", • ..:.. Ic.:':" __ .. ~ .
C A':~ b.. '~e0r.E.,l·::,'J c a~i[;~.e 0" 8.tc;acl - of' 24 <3.1(-;' a ,~c'1. n 1.":1":] " 01' Ool' C . G the c,:)Y-re(';',~~~nc t:- t;·.E- l i;~t C)::;-Z':·:"cic:rt 81~d ,.~ll'h TIl11::.-':> el~ .. . .. er·e .~ . • 2 y8 re· en t c~!d ~ ,, 2 "e:'-'c~ e11C , I'f:":- 21.;8 S t i -\/~ l:T 0 P.~:.-:e.'" S \.:.Y'b - sJ .. '3 t ril) 1 .. 1 tion drt ta • - 11:(' ,. l'e S S 1 ~l ' e - ~~. f'; ·r i :) u t io:. '1 ------ -----_. _ ------ .
data liLve 0(;81: c)rrectec_ tJr tt.8 _p'iY".ci>;l ~ffects --:: . .f I J ;6 s· ,';.ppo rt .str~t~ L1 ~.:r:J.t; tl-:.e f'ree - 3b"eil:-'1 '.rc::..ll"cs of .static LJres8u.l"1e and c...c.-·~-l:.lt"llc .IJ~""eE~Sl).re 1.J ... .Jt)i'l r.·:·._ier- t·:.-:e presrlJli(:} c8cfficierl'tf-· r'€!'e ~~&.sed v·erJo CGtc)~")r1j r:scl f ':c::",: a C31l1~\Te~/" ai' the flow in t~e test secti~n wit~ lb8 suppo~~ ~truts a~d shlPlds ::n!:'talJed . Sor:'10 ~:1;all l' · "~G.J e7'ifctQ cf' the stY·r!.ts 0rl ·i.:~1P. Sr )d. 2:'~ ~· isG load :lj.st:ei.1··l.,t= ~ \:)r: rei:'=J.~n. o rI'rlo?-e effE'cts 'Hi l l be d::'3 (,u ~'Jed in -:he spct-'tn:-:. ~"'nt.:;.tled il H3su 1.ts a ne. 1: 5. sC~..lp.3i")n . \I f ~:-le effect sf i-1:c trtn'le~ ',· · filJ.s 0rl t1.-e ~ ·.)[~r;~V~Lf'f· I )[td d:L "ltrl:')utj O~, \"a~ cO:l<:idered :'.nC: f-~u::d +,8 be vcy':~- ~:·'D.ll ; r consoqyentl: , trw<)8 c~.o..ta Ci:3 r,re"enr;E.d ~'- ~.'E lJl"lCCrrectecJ for -cunrcel - ','mll ::. Ylt.erl'ernnC8 .
Y :i nr lift, C'"ars-c-:,'d ~t·1.\:'" (-:'~7'(:e tF::'~t resl'lt8 ).- Th e lift c!.1,:lr2.ct0r - i~t~c~ 0: t.l-;.e '~l"~rlf" :.1.":' .;. f ... nctj.~r: ~J_-' &['E l e ~ACA ACn No . l 5G I O C ONF:::rYC!i? lAl 9 of atL- •. c { 8,nd :.lach nlUtlber eire s110VJn l:-l fip"t..'..res 6 and?
Firure f is rresented to indicate hy ~he ~catter of the teEt ro1nt~ the precision wlth ~~lic~ the data were ottaIned . 'T'he same data wi.th the te:'!t - ,;:)oint symbols re'11,ovec and. with the hori z ontal] i::1e::; (:rawn for C0::stant and even vaJu8s of' a~r-le of a ttac~: are given in fi7ure 7 .
The variation of ma-:-:iIl1u1TI lift cC'6ff':i.cient wi. L. ':o.cl1 n'.::':1ber is ~L()vm 1n i'ir:nre d . rrhe maximu:71 l i ft co eff2.c i:~'n t i ncrep-.s'3 ~ v:} t~'l inc rea,sin{' "ncb num'-Jer und 1 a :,~<~cr mxmber of cl):}ut 0 . 30 if' :'eac}wd . ~Lis Ln.crea--:e Gan pr,)ba"o17 be attribut.f-J( to 8. ccm.hin8t'~on of ::e7:':'101de nwnber r 8,nd ''i ]''). '1uFloer err-ccts; 1'10V eV,'j-' , :.1:'3 Ee-'molds nur.'ll')er efr ,c t ae pr)bab l ~f .:'rerlo'!ina te 8 in tbi s re~'ion . As the ' ;ach number Is i_~lCI"·8aC!,;:d. :':J.:Jnve ) . ~O , t.~~:e mD.j~il:'\"J.!"!1 ., ift c')eft'lciel1t (ec_'e2., G3 s,t 8.~ l!!cpr ·a ~in.:ly r , :n ~_d l' <' .te '~L1t il a ?~[l,ch nu:nbc r
of i.11 ):, .. 't C' . 55 2.2 re8.cr.ed . I:1 I.:~:"e T·ct:::ion ~ct'''Jeen l\·i = 0 . 55
ancl :; = O. c25 tl ~· e r~8 ce of c.1e';1IC£i~{~ OI~ :'~1a~~iYil1)2!l lift coef -
f~:~':'elJ.t ', .. .. i~h l\Iac~. n~12"l~ er it: c ~)Yl :-i(:c .. ·r .. l~ly : educea .
?he lift - coef'fi(> :~e~t c 1rves ').:' f'j cure 7 ~:re p.reser::ted ae-aL. ':'n .i'~ re 9 , ~~otted to a co~"l on ~'T r le. - of' - a~~2,ck C'-;a~.e to 12.1u!'l'Cret::; 7 ore e:eal'=.~ t;'i.C C~1,'-flE:i.n3: <_aro.c.ter 0; t' G E: tall a;-' -::,';e ,BC:' m.:nbel' iz E'C!i'e:a"Ec. . ~_s -:;11e ;'iO.'?-11 nu:::~o(.r i~ creases a!),}ve 0 . 30 'L.:-JE" tt.!.'l,:lG 0_" attac': at ',-:J':C}~ tbe ";j!lCS sto.lls prljp ' re~~~''-el:]' L.c~Ilet:t.&·cs; also, at I.r:o.C:1 DU-:: ) E;T3 1-;e' ow (J . 55 t:'E ": ~alling c.lt}erle and t118 anGle for y,o.riy'tu.: lift are apprOXi~,lLttely the same . F_t ,TaGb nu.; l"er'S above 0 . 55 , however , tl.A md,;J,lTIll_l"'I :L't (;::lef'J~:_(;lent n~("'Y'C:: a" a-" ar<--lp of ,-l-C'{ 0 -, ," l"~C '~ · r.·1t:>r tbrn r:.-t oJ l,;. J lA._...... ::- 1.... ! J. e ...! . ~ d 'J 'J cl . '. _ l "" -"~ ,..... r . 2. f~.L v' _,:;1_ l .. ..:. d.
at ~bjch pro~o~nc8d separ~tio~ nf the f:o~ be ins .
r.JerE; -::lata i;lr'lcatG t -1at fJr' 8irDlanes "', ~ ~h w'n[s s:_"~ 1,!' to 'c hc tes-:; ,':, ns: tl:1.el'(, e/,i~tg '1" r-.'tG 1 c::;::eeG.:3 a r-nnge of .:aximu.'11 obca:ina"0J E: li.ft cop,""ficl Ent . 'ThJ.~ Y'3.n'·e 8xter:c..f: froL t:1e lif-: c')effic ent c')r"'e~-:)o~,c::':l "" to the J.'1::.t~.al st;rlJ (~UC:-l ~,'1 p',') ,v;: by t!:'>e lm"e:' (~a':'ltcc1 curve of f:~[llre 8 ) t') ttat ("ol'rl:;~rJnn. ~'5. nc t) the ac'tual : o.'·ir.:w" l:U t cceff:i.cien t of' the \Jinr:::. :,t t~e 1 :)':,.1<:' ::' T:]YC J~ lii't c0ef:'j~i('nt cJrresp')~dtn~ tJ the c~ange i~ ~lJ~( ~~ Lhe 15ft curves of f i l.:re CI , il1cl'eases in ~r:abil:~ty cl1'e ~l':::'nlaril:T to decreases in c.o"rn"Ja:::~ e.rJ.rlG ur'e L.::el:l +,0 Jec;ur-. It might :-'f' e, pected tI1CT'ef )1"e ~J~1C. 'G at hj gh SI<?6dc: the (:.mount of elevA. tor contro l avc::..i..la'J] e 'i·QUlc .... he an i'J:)ortm.t factQr in dotE"rmin':nc the T;'laxjmu":l lift coeff~ci8nt obtainable (rerE-renee 4) . Thus , an 2.. i r?l<..ne witl'! a lL·;i.iteG. ano'Cu:J.t of elevatJr co ltro l r:l'::.r,:~':t ".Je ca~:3.tle of rcacrine; (]rl A.LCle of at'L,[lcj-;: only a fe w C01'JFID~:d :IAL 10 ~hCA ~CR ~o . LfS10 '-3.er;rec.s aCJve tl'e ,-ta ll , aY!::1 ;:Le '·If'.:·irc.1?': lift c)ei'ric:i.or:ts
Oi)t8.j 11R:lle mir'r- t '')e ol .. l~{ .sli~".~- 1,11 ~r·ea ~Cl ' t,l~3.l1 t:"'Q ~e
I'C':·To"e'.ted b;r the lO\":81" (zshocl C;lJ.~'ve o~' f11="'1"['e 8 . Tail 1"") '~"f'( t:.,1p' ~_C' a1ro l:'..kel;T to OC:Cl~:;:' ';:rlon tho flc)\"' sor ' r-ates :':T'.;:: :'10 '., i 11';., 80 tL2. t pilot4.:l[ tecr:( iq:.le C:l~l.rO~, lw 'Jv·::;r - loo~cd ~s a pocsib : e de~er~inJr~ ~actor . Pin~11~ , at vel': }'"licl. ~::1.8:~ n1.r:lt.,eI·s ~ l is P08"'::"I.'le tllat <'·lctual :1.nstD.1.'ilit·:.~ ::Ji"ht ::0 e:nc ,:y,nte1"ecl.. , in I;,L'ich ca,."p. }'i:"h an(=1c~ ::;~ at: .~Ll.ek r.:. _\..~. ;'.i:!:,l1 Jifts :.ni::.ht be obtg.i.ned .... 'lo..('/\,rtf'~1.t·l.y 1"GS£I.1'ulcC'~ oi' t:-.6 c.or:.tr;)l r)C'··(;l~ .
~")am-rise :~oad d~.3i~::'.i..but-lo:~ .• - Srar1',·i.L",O 10:"(-;' c';.J.::'tri - f' ~ -.- 'l'-:-n r ! ri:TA c: f .""'I';r. - r - . '-r--:-.,"~,:,~·~·; -l:;-~ - oJ] ,r:J r" l ...... f' " i r,"" r (, ... ..... , ... ,'. , _ f'·, Yl"" e b ..... ... v~ J •• _ v~; -' __ J. '_. .,L ....... ' u_ (.\,.. ............. .. \ _.1._(.; • .!.. .~Ct.,_ ..... .1. ~ c08ffici6nt 'l.:nc~ :','1::::'1 E1X,1' cr :;,: E, .""~"r:.:;:--~ i"l :i:~'1 . ::'·'~ lUG l~S li!~-1"LioI!cci. p!'sv:,oL~'31~- c;:; ... ~ prir.f'ij"'E'.J. (-:{,'''e,:"t of U".e su:t::porc SC~Cl::.tS (v!1_J.c~1 Jf' :.0 irlCY'CaSe the e_~!.'(ctl"'TE: .-:-tl"€.a~· \Tf·locit:\;r ) \'t3.S aC~.)l.mteJ fe'I" ~)J ' ca~' .i.1:-rL~.tiE.s t:':0 u1ur.ol .lith Ll'1C stY"_Lts i::1s~c..lle,': . 111~' ~e 10e8J O;'j·I' ... Gt ()f t:-l,. rt:'l~r~:s Is to t:-:e J.i~jt B.t a t~ ive (.1. urH?,;1.e Ci." r .. .I~t3.C~ L'.i 3. 3~~ ' .1 £::r!1::)l.lrlt a~lCi () ;;"J~')I:!.-lCr- d ".J.i~ll-:' ~ .. i8';c,.:ytlvr: ':;.'! ',_'.1-:'6 -:-Ll.fl 108. ~~':1~~ . T: ~s c..l:.t:rt~J)r- ... :nn.~vp be scef'} u.;:; & f ... il) 1}::. tl .. e Cllr~]6~ e.i' :·:....;'·1.Are l(j :~~:; = 0 . [5 . ''::rs c.:')}.lC. <'l:(,O.
o/'~ da=<t.lcd curves of .,;:'irUI'8 10 rt9rese~t t~o loart ei~~~~tutlon s t 11:1:e e'-r~J8Cl of .t l[,lJ.re Il f:l~,:'~Y"'~~;"J~i~e 'C 18 ('.~lnrl[e~ :'r: s],:,[tr1.
l:Jl\c ~=_r~r~ t~;I:?t .. "C'r:e ~'-'1'~!C. to 08CI',r -:~ t~-3 ~ .. l""':~e··" te~·~ ::i')eec10 0 fTo :~~gI1:t~'jC~1}1.~ c11'ln·.~f-8 In t.he <:;~··~l.n lOc..<1j.1'1~'~· \'J~re f")U~'l(_ t'J ()C~"11r) "bel()\~ t:V1P ::~-':a . ll at a:r:7';- o.r t:.,c ['~':-G'J(!" c-:' +-be .l:.e;~t , t e 'tJ r~:! 11 "\iY:"_ 0.)1 ("! Ii) C;: Via '.Fe s \; CT' e ".rc l1. c r;. !~[...1' 1 i ~!1G Ci. ~ \To:r :.'1;:: C rJ rJ. t c r pal"'t C<:' trle l,,~:'nc . Cha.:.~_~~cr i?l t1:o 8"'art lcc...·~ll~l""1' V·lE,r·C c',.)ser':Tcd to t~1.1:(, P:,l"O rLb-:ve C}-;(; ~·L~fh - <Jrpt.c <:;.; 0.1:;' , ho'\:e'l8Y' , t::e c.e':ttt-;r of Jo.J.C! . be:l~17 :-:hiftcC G"L''t;'.';)::-lrc:' . :110"'e CLLI:P-''?!
at t.l'.e 11.irh(:.r CO[;0eds v~~el~0 fOUrl(~ t.() ·,.)8 ·.-;~):~el att:~ . ~~c l·J.ygest corlr0Sr)Ory.:)i~J.[ inCl'caS0 =-11. 'I (rtc:i~'1.;:: n10v:~,;nt ·~J.t t}:16 TO ,)t (for c onsJvar:t J.ift) ~'i[,E: ~':' C';;m:l t.n be :::~b0:]t 1(,: ]EY'CO:C.;.t ct a :.~8.ch nll'.l~~el'"J Q.f 0 . 55 Llr;.cl ~t 1.~ ~Jr·~ 1 or~)::1 - i'2~'lce jrlof.[,i8~1.e~ t c·f ~l.l)Cltr:; 0 . 95 . 'T1-!C e}'~c..ll1~\'C8 1.11 lo9..C~ L:iq~112.1"'1..1t.:.!:,,(jr' d,lJ.G to sta::'ling at J.C)I. .' S~)(;(;(s \,Jf:re :C()··le\!:~ia-s J ~rCGr c;r..un tno::'6 8.t :-li~11 speec~s ~::iJ .+:' a-:'le llot 0_" J)t.ll'lt.iG~!J_.~_l·' ~:1il..~r·if.i8c;.rl ce b€..ca~lse t:t. .. ) tot 1 lift cs.n~·~~·t be l1aJ.l:t!_:! nCr) ")8Y,)l1C~ the ct,a 1J _.
' ... C0ltl r(~.ri f~c.n of the r~';'-J)[,~.'~.: j.;: ntall'\T C~E'tc~c::::~~ ned. load
distribution c urves at ?.I = 0 . 1:0 vvith tllY"0 c&lcuL ted
by tile J'lctLJc of r..3fere~~.c:e 8 i ':: s':IC' .:n in rif,u'''e 12 :!.~or values 0/ wIng normal - force c~~!ficicnt o~ 0 a~~ i . C.
NACA AC:l 1;0 . J EG 10 1 1 T T:le a"'::~ee:;le:.1t 9h:)I!Tn i;-' t: T'ir:'2..1 0-:': ~l:a t existing Ll tl1e nn~ t311{~ci Pi.lT·t of the 2.if t curve::: .
r:.~nd - tunr:el tests of a t8.)erec w:inC o:~ ITACA 2"'O - s0ries a.l.rf·J:~1 sect:'onq c. t :·~ach D.'lnbc::"c r"-'.nr-;inc fr011 0 . 10 to 0 . 70 ha,".T8 3}-:cv~rn that : 1 . The m['_xir:mi~ lift c.J~ffi c5. c..nt f'':'''r'':l'~ iY1creac;ed "d th irlcreas ill.C I.:fi.cl-j ~·lU.l'E~~ ~l.. up to a :.=:. .... c}~ .I.1'·jJ":~C e.L'l of r) . 3 • l'iEJ t:c.e :I~cl; n'lub er '.'.'8 s hie rea~~ec. s..bove t1'i 8 v,~l.U6 ::-,;i6 r,13.xi - :"1um lift ~Q8ff:i.c~(,:ilt G.6Cy'ea-:ec. r[.piJ.l:~ .
2 . ;,. larL'2 P8c'.<ctin:,,: J.n t·.}F' rate of ,'ecrensE. of ,laxi - 1:11).111 li ft .; )ef:':'c:~ cnt ':;i t~l ~.lach .1Wt:,e::· occu:::':;.·er::J. in tile I.tach :'--l1'.rrl~ -: cr r8.~··e of 0 . 55 J~~ O . G25 . r1Le t'~11J el ~a~.ll nVl:lcer of 0 . 625 '.I:tS tlle T.ir: ' t ,-=:t val~e tl'~at c')u1(1 ;:,e obtained at the l.~r[e ae[J.es of c..tt·ac~ requisite lor :''!&.;"L1 :Jl 1i:'t .
' 3 . t.t i'ac~ n'~iT!'''sr~ ~e.ow J . 55 t~-!€ o.!}-;lf.S ~f at'c«ck at w£'icl1 ~;h6 ma:\i~uJ'l ::'i[;:; coc.:'·~icien,. , \ 2.s :"eaC'~·.ec. an(~ B.t ' .'T; '.ich c: t '1.11 ins 'Jce '-n'_~ec ';>=:1 c- a~·'roYi!"".~t te 1 v L-:e sa",:e . At
r"ac::'-l r..uj""'Jers 'lJ0Ve o. 55 t~1P an'-le 0:;: .... [4 t t;a('~~ a t \:h~t;h tr.e
l1laxirn:;->~ 15:t cQf-ffi(':"er.t '7:.'~ re8.c>'·(~ ';as 20 to 12° bEyond r T tbe fll.r 1e at:("1ich t.1e 1d::'nc i:1itia11: -':;8.::'1 d .
4 . ~o si~nific~nt chan~es in the R)Rn 10a6 di?crlbutlon occurred 'Jelon t:'LC ~~,a11 at arc of :Lc s::;ecds tested .
E . '~oc~eratc chan 'E:.:: in t. v "'l,HI :!..08.C< (i-:t:'..!..::.ut~.on Occ·t..H'red. "::1en "::te .J';.n~' 8tal18d f~t ~_r::h c:p"'sc the cor·ter J i of 10&(' bCU1[; ?LiftF"C ::nl-':b:8.rc.. :":.~ lr ... ~'-·Cf't ~)rres.pondl:1[
inCl'E:8.::e ~n '. e:-:c'Unc Ylo:'lent at r.e ~ r.:: rao:' f'Jr co l:.:'funt
---~ -_._ --- ~!ACA ACR IJo . L5GIO Jj£ t ,. L:S :1.)( vt 10 nerccnt ar_d oGC'.v_rre0 at II. i'.~ac'"" EU:rJ."er of O . [)~· !3.11r'! 8t a ping nor"lal - foY'ce Goefflcient aI' a-t)out C. '::15 .
La~Fley Mp~0r1Rl AeroLautical L&bo~Rtory Ea tio~hl ~dvisory Co~~ittee fo~ ~ Er~:2ut~ce L~~~l~y F1016 , va .
COIT.::'IDENTIll.L NACA A CR ~\ro . L5G10 RE,F1RE JCES 1 . ~=use , Thomas C .: S()mG Effects of Reynolds and fiach Numbers on the Lift of an :JACA 0012 Rec tangular 1~ i ng in the l·ECA 19 - Font Pres~ure TunneJ .
b NACA CB No . 3 29 , 1943 .
2 . Cle~ry , Harold E .: ~ffects of Compressibili t y on r.~8.xj.mUJn Lift Coef1'ic 1 ants for Six Prope ller Airfoils . ~CA lCR No . L4L21a , 1945 . '
3 . Rhode , Richard V .: Co r relation of' Plight Data on
Limit FreS3ure Coefficients and Their rt61ation to High - 3" l3f.:d Bt:.l'bl:tn[ anG. Cri tical ;1'a 11 Loads .
HACi-:. AGn l~u . L4127 , 1941~ · .
~_ . Niss8n , Jar. ~e3 1.: . , a.1d Ga, leLerg, Burnett L . : Effect of Iviach G.Dri P.ey'1.o1os i~ur(lber[-' on the Power - Off Maximum Lift Coefficier..t Obte.inable on [.l P-39N-l Airplane as Detdrri.ined in Fli€ht . IJACA. ACR 1',0. 41"28 , 194h .
5 . Goldstein , S ., 8nr] Youns , f... . J . ~ 'lne Linear Pertur - bation Theory of Compressible Flow , with A?pli - l cations to vdnd - l. unnel Interference. R . ·Il,: F . 1'10 . 1909 , i3riti~h A. J . C ., J.9~3 .
6. Lo tz , Irmgarci ~ Correc tion of Do"mY/ash in 'iJind Tunn~ls of Circular an~ Elliptic Sections .
JACA 'I11: No . 201 , 1936 .
7 . Thom, A. ; J310ckag;:'7 CO"r.:.'cctions and Ch01C:Lpg i_n the
~, . A . r.; . Hi ... ';,ll Speed Il .l. 1ne ;t . ilOp . '\fo e _ero 1d:-l , u . "t " l R li -T '913
!3rl lS: .L . r~ • .u ., I,OV • .J.. 4- •
3 . Anon .: Spa'1vlse .n.ir-Lo~d Distrib'.J.tion . A:TC - l(l), Army - l~avy - CojrJllcrce V OlYiT.:i t t;ee 0_1 "~ircrL.ft R -quire- menta . U. S . Govt . ?ri.1tln[ 0~fic6, April 1938 .
CONFIDENTIAL z > > () > () :::0 z a r-' ()l Q ...... o ":I:J f-o. ......
OQ line Clbouf 4-l ,I solid a camber ion chord t fib -- vo/u Root AlItOtlAUT ICS rt; mean ADVISORY fOl W'/nq e or th ~25c.
chord 23009 NATIONAL COMMITTU orifices.
230/8 pressure __ MeA ~Tip -- -'~50c.
/8 I conduct seetion- -,:-- 3 . wing pressure to TJp of ____ of' out used Root section-NAD1 ~ locafions
~
CONFIDENTIAL and CONFIDENTIAL 7.fi , , 144" - , VJ ~ "k!sfs # 12.9" dimensiolJs
------J--~
, I o -J
~~+I force
wing 9" .
for.
=t
u:ed Principal 14.4~/2 - ring.
I.
distribution fiJi " 'I' .
Pressure-orifice stations figure fL4~ .
orifices NI - chordwise.
of .9' . .
------~-
I~ Typical ~- or ~
-~-
twist ~XlS
/+"01
z :> () :> () ::0 z o (J1 Q f-' o t-', :> r 'XJ t\) OQ ~.T conduct to used assembly strut and AL TI manometers.
boom to DEN FI ,N CO tubes showing wing of pressure view Rear 2~- CONFIDENTIAL Figure
"'"
.
z » » Q () » () ::0 z 0 l' ()1 f-' 0 'Xl ~ iJ.l oq I I ~ ' ~ ..
,1"t4 " • fbf ' .....
'- force for tunnel the in upright mounted measurements.
wing of view CONFIDE:NTIAL CONFIDENTIAL Rear 3.- Figure NA CA A CR N o. L5GI O Fig. 4 /' V CONFIDENTIAL
/'
V
/V
V
/ Q:
/
\ l..
~ V
,5 -Q ~
/
~ c:
/
V
'ti /
........
Q
V
~
/
~
/
I
V
/
I V NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS _ / CONFIDENTIAL
V
o
.2 .5 .6 .7
o .I .3
/'-1ach nu.mber" JV1 Van"a!ion or ayerage Reynolds nu.mber wit-h /Vlach number.
C; = 2 .0 reef.
.
z > o > > o :::0 Z o r c.n Q ~ o "%,l ~ c.n OQ in~talled CONFIDENTIAL struts support forces.
image tare with strut wing of CONFIDENTIAL inverted of determination view for Front 5.- Figure NACA ACR No. L5G10 Fi g. 6 1.6 CONFIDENTIAL 9 ~ ~ I . 4 po ;~ ~ ~ ~ ~ , , /";) , /7. 55 9' ~ . ~ 'A -.....
2 I.
/ /( I ;' . 1/' , ~ \ 5.4t: c:f ~ , , ..4- / ,.
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0 I.
/.3 .2 0 \iJ" " ~ ,T I / \
r'ty
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~ := )1 ~ , ~.c; .d- fj" r~ ~~ ~ .:: / '
X I. ill
- 8
I /
~ /
;\II / « X / O 'Y I I-P" 7'1 ''2'S, ( appro x .)
I / I {c.85 " , / ' p; IV I V 0 . / 5 I I 0 . 20 , ~O ~I 4- ~ I -f-
/ i
. Z5 <>
-
. 0-:> , . .30 6.
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./ ~ ,"4 5n / I . 45 <J / / I ;' 17 .50 , , / / I,j, ,
/ ~
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: :L r; . 675
D 0 "(6/ I / Q I .70 I / /" / I / / I I.'
/ I I -z.os , I I / / I I I I I / I I I I / "'>' • ..."
, / ./ / .r r / / 'f / / / / / / -.::: r-' /v I ,r I ..ts/ / /i : 5{J ,
rr: I I
6 -R .
"- / NATIONAl ADV ISORY ,;: ~ /" " .--17 I COHHITIEE fOIl AERO N AUTICS _ B -...
/0 . 60
I I I I I I
(For a = OQ ) 0 ./ .2 .3 .4 .5 .6 .7 M -12 -8 -4 0 IZ /6 2 0 4 8 (fo r M =.2 ) Cl::".l deS' CONf i DENTIAL Figu.re 6.- Win g lift coe fF/C ient a s a Fu.nct ion of an g le oT att ack and /Vlac h n u m be r.
NACA ACR No. L5GIO F i g. 7 1.6 CONFIDENTIAL h / I. 4 V_; )L
v- /~
lt~; -" (8/ l-----
1/ l!
V
z I.
, ,
ff
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II NATION AL ADVISORV
- -- z CO MM lnn FOI ... UO . ... UTlCS.
.; I
/ / / /
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/ / /
-6 V_ I
l( IV
- V.
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L V -7
1/ V
6 - - '- V /~ -10 ~ ~-
V V
-- ..
CONf i DENTIAL .3 .4 .5 .6 .7 (Tor cx= 0") 0 ./ .2 M - /2 -8 0 4 8 /2 /6 20 (Tor 10=.2) -4 cA , d eg Figure 7 - Wing / iTt coerficient as a function if angle or attack and Mach n u mber.
N AC A AC R No . L5GI O Fig. 8 I .
1. 6 I I I CONfIDENT IAL -........
i'--..
1.4 ~
V ---
~
\
"\
/V1aximum l ir!
I. Z coeffic i ent >
\
/
\ /
1. 0
~
Z
L i ff co er rici e nt
-"" \ ob ta i ned a t 2 a fo .,30 ~"- ./ ~ above fhe an.x1e OT .8 /' ....
"- attack cd w ich
C inifia/ . sepa..rafion or 1' "
Lmax.
the Flow Trom the wing occurred .6
p-ee rig. 9)
.4 .2 NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS CONflDENTI AL
o
.1 .3 .4 .5 . 7 .2 .6
M
Fig ure 8 . - V a.riation oT wing l77ax.imum li Tt c oerricienf with Mach l7L.L./l7ber.
NACA ACR No. L5G10 Fig. 9 /.6 CONFIDENTIAL
1M 1 rJ ~n
1.4 "- .40 _
~
t-// I '/L I~\ ~ I P I.Z 1\ 1.\ '\ .50_ \
~
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A .55 __ ~
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,~
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,-
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II
/
, -2
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w
); -.4
Jo/
NATIONAL ADVISORY COMMITTEE fOQ AERONAUTICS V /.
-.6 CONFIDENTIAL
~
-/z -8 -4 16 24 28
o 4 8 12 20
CZ, deg Figure q- Variation or wing lirt coefficient with angle aT attack Tor .several Mach numbers.
NACA ACR No. L5G10 Fig. lOa, b Frac fiol7 of semis pan , --/;:, :Vz (a) M" O. 20.
I. e. r--
-
.'-N=1. 2 8fna )(.)
-i-
----
t- ~ .......
I.~ ~
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r--..
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tl:.!! I'--. 1"---
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r--- r: =93 "'
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r-- --
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~ - .8 J'.., ~·above sfall)t--
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II) I::-::: ~ K j ~ (t'"bove stc!
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---
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-
-
Z o ./ .2 .3 4- .5 .6 .7 .8 .'1 1.0 Fraction of semis pan, lz (b) M = 0. 40. NATIONAL ADVISORY COMMITTEE fOIl AERONAUTICS CONFIDENTIAL Fitjure /0. - Spanwise loa d distribution curves for several values of will,? Ilormal-force coefficient Qnd /Vlach I7wl7bcr.
NACA ACR No. L5G10 Fig. lOc,d CONFIDENTIAL /.2.
~1 I I I r- ~u" /.0 t-- C =/.06 (max.)
N <::: F ~- u
- ~l:--k
f/:O~ ~ ~- /.00 r-.:::: .....
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--'> .~ -- G:: ~ h:---- I ~=. 94 _I-;--; .~ t;:::-:".
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r- - -........
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-
-
t--
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r-- 0 ~
V
I---- :2 -.2 o .3 .5 .6 .7 .'1 .I .2. .8 /.0 rroctio/7 of semis pan ,
~
(c) M=O . .50.
\JIu'" /.0 <::: I=-~ 1'--:..- _ \.l
-
eN = .9 S I, .1 .1 - ....
~~
.... ---= - (opprox.2°obove stall) .8
-
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" A ICN= .95 to-
--
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t---j-... N.:::--:..----- .... I
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rL
r- :-- I--........I--r-:-........ 1 '" ....
r-- --r-----...... \
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-
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---
-
0 r--
-
r-- o ~
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y.
-
-.2.
o ./ .2 .3 .S .6 .1 .8 .9 /.0 Ft'oction of semlspan , o/z NATlON.U AOVISORY (d) M=O.55.
COMMITTEE rot AfAONAUTICS CONFIDENTIAL rigure 10.- CO/7t/l7ued .
N ACA ACR No. L5G10 Fig. lO e,f CONFIDENTIAL 1.0 r--
--
.8
-
~ ~ r---
~~
\.J'=
.. ~
---
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k :::-- .6 CN:;:;·85 s;::: r- --------::.. VI) - - (~P'1x..5 above sit/,
rL
r--- .~
-
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, ............
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-
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r--- --.~
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r--
---
I-- t- ~\ t:::::", '-l r-- r-
r---
0 ~
t2
r- I-- -z -:2
o .I .2 .3 f1 .5 .6 .7 .8 .9 1.0
Frac liol7 of semispan I ifz
(e)l'1=o.60.
/.0
-
.....
....
1-- ....
l:-- .8 ~v ,CN:;:; '&)
- ....... ..::::-
c,v=.~\ ::::-~ (opprox. 4 'above stoh 'I) \jt::
--
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r-r=:- --
pc...:
-- -::-
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-
'U CN~85 I I
-
~ .: (approx. 6 "above 5
-~ -
r---- -
---- r--
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r---
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~ ~ .2
.2- ~ t::::"
--
t;:J <;) ~\
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-
I--
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r---....
-
0 -
-
0 ~
-
j ~ -t--- ~c.
-.2
o .I .2 .3 11 .s .6 .1 .8 fI /.0
Fractlon of semispan, ~ NATIONAL ADVISORY (f) M = O.b25.
COMMITTEE FOR AERONAUTICS CONFIDENTIAL Fi9u re /0. - Contmue d.
- ~--- ~----~--- ~---------------- - NACA ACR No. L5GIO Fig. 109,h 1.0 CONFIDENTIAL .8 ~ t-- - _ C/{=.7 (o,IJ,lJrox . 2·obove
-- sldll ~0
l .6 ~ 6- - u
-
F'--t--t----
-
-
" .....
r- -
-
-
'=
I-- -
j r-..
'lJ .4
-
.......
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-
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"
r--
() c. ........
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\.)
-
I--
-
-
I-- t--
1\\
.............
-
~ r--
-
'-l ~
---
k2'
I--
-c
-.2- o .I .2 .3 11 .5 .6 .7 .8 1.0 Fraction of semispal7, -t;; (q) M=O.65 .8 1I1~ .6
U
...
1-.
~ ff CN=-1 .~
-
.\.J
r--
-
~ -
"-.:
r--
.c.
'U
---
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--- r---
\J -
- r--
-.......
-
~ ---
r--
~ r--
0 -- ~
() -.j
L
;c I--
-
- .2 o .2.
.I .3 f1- .5 .6 .1 .8 .9 1.0
Fraction of semispol7, tz
NATIONAL ADVISORY (h) M= 0.7.
COMMITTEE fOIl AERONAUT ICS CONFIDENTIAL • Figure 10. - Concluded.
.
z » (") » (") ::0 z o (Jl Q I--' '7:J \-' I--' I--' » l' o OQ several ISORY AERONAUTICS for ADV .7 FOIl NATIONAL
.8
COMMITTEE .7
I
!I b/.z J .6 coeff/Cieaf.
spo/lw/se load distrii;utlol7 v .
.S 0/7 semlspan of :4 .
S
tlon
C; llor/l7(//-force
T1-+-~-1
CN:· .3
rrac
I compressibl/ifJ will9 I 2.
of ~I . of M':40·}· t I --M-=-.55 _ I .I CONFIDENTIAL values Effec - --t---t---+------'-- /1.
1-1
o
°F=i=~CO!N~F:I~D~E~NT~IA~L==~1F~~t-~~~~~~~i==b~==±==h~
. .4 z.
/2
G l::::: S( Q.) ~ \.) C)
. .\J
'I-.... ~ ~ ~ '"'-l ri9vre
\.l\S o z > o > > o ::0 z o l' CJ1 Q r-' o ~ 1--- r-' l\:) OQ /.0 \ 0.10.
_ :::::"
-
'\
~ I.
~ M:.
--
I
- .9
at
- distribution
~t-..
•
I
/.0 AERONAUTICS
--
ADVISORY Experimental_ Calculated ~ I load .8 FOA ~
- -
I and NATIONAL I r-....
.7 COMMITTEE t-z.
or "-..
co/cLI/ated
-
......
.6
~ and ~ ...
....
I-...
.5 semispon, coefficients
::-:::---
of
f::-:::-
-
::::- experimental
-
-
---
of .:5 Fraction
- -
l1orma/-force
-r--
_
--
.2
-
wing
-
CN=0==r\ CN=IOY f----
./
COnJfJariso/)
-
Tor - CONFIDENTIAL - -- CONFIDENTIAL - /2 f-- r--
o
o
.6 /.0 .2 1.2
G ~ ~ IJ ~ ~
- _\J .......r curves
~ ~ 't-4 ~
~~.8
Figure J