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1 4 1 A6 A TECHNICAl. NASA TM _7 2 7 15
MEMORANDUI_
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< WIND T U N NEb'FLIG HT DATA CORRELA T ION FOR
=- TH EBOEI N G 7 3 7 - I00 T RANSPOR T AIRPLANE
BY F R A NCl Sd, ' C A P O N E
AU GUST 1975
( _'_ , ' : I_-_'-_-72 71 _ ) I_Y_ . _ ' ._N._L / "-TT_H_ DA"_ _ , ' 7_-3 1 _5 1 ' r OP_tATIO_ V _ TH_ F _ e _.IN O , " t g_-_ T_NSp n _ T _T_ T _ZAN_ ( N_gA ) I? p HC $ 3. 2 _ . C' ; CL ^ 1 C .nclas e , 9 / "5 3 _26 2 This inform a l documen ta tion m ediu m Is used to provide a oca le r a ted or special release of t ec , hnl c a l Infomation to s u lected users . The contents my no t meet N , A S A for ma l ed i t ing and publi o etioh s tand &_i, m ay b e r e .
vi sed , or m :l b e incnrpor a ted In anot h er publica t i o n .
NATIONAL AJEII O NAUTICS AND SPACE ADMINISTRATION ' : q
LANGLEY ItESFJUtCIO (ElffEII , . HAIdPTOM, Vdt _ NIA
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I . Report No. J 2 , Govemmen ! Ao N m m n No, 3 _ fl-eci _ °$ _t_ m NO.
• NASA TH X-72715
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4, Title , m KI SuI M it l e 6. Re _ A ut 'i , mt 197 5 Wi nd T u nn e l / F light Data Cor r e l at i on fo r t h e 6 . _ m _._ O _ , _._ C _ m B oein g 7 37-1 0 0 T ransport Ai rp l ane F ranci s J . Capone 10. Ww' k Unit No.
o. Pa r f omt _ O, Imhum, _ N _ -. ta x i k _ vm 505-0A-I 1 - N1 NA S A Lan gl ey Res e arch Cen t er .i" C om . _ 6 , C . _ . , N o .
_ , Ha mpton, V i rg i ni a 236 65 .: _ • 13. Tyl m of Rqx _ t a ndPeriod ' CO Wa l l d ,; 7 1 _ 1 2 . Scorn fUl _ _ md _ T ec hn ical Memor and u m Nat ional Aeronau ti cs an d Sp a ce Ad mi n l s t r a tlo n 1 4 Spomortn0 A Sm _ 'y COde W ashington, DC 205 46 15. Su p_ k _ NO ra Sp ec ia l Tec h n i c a l Inform a t io n Re l e a se, n o_ pl a nne d fo_ for m al NASA publ i cat i on 16. _ A b ri e f wind -t unnel / f l i gh t da t a correlat: o n fo r t he B oeing 737-100 a i rp l ane has been m ade. The w tnd- t u,,ne l da t a w ere published i n NASA TND- 59 71. Th e resu lt s sho w ed excellen t a g ree m enL between win d - t u nnel an d f l i g h t t r i mm ed drag polars a t M a th n um bers l ess t han0. 67 . The _ tnd- t unnel dat _ predicted l arger drag incre m ents due to co m pressib i l it y a ud a l l ft-curve slope about 9 p ercent hi gher tha n flight.
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.. Key. Wo _ .. C S.m,m _ k. M ,(,)) ( _ *,c, tmo.v..d _ ,n, d ----- 77_ O i , . , _ , _ * __ A erod _ m am lcs Unc la ssi fie d S u b s o _I cTr a nsp o rt Unl im i ted , , Wi nd Tunnel D a t a • Fli g h t Da t a U n cl a ss ifi ed Unc la_ *Av _ lald* from }Theflotio _ !Techntc4d Info 0 mlltt _ S lndce . $ _ ln Q f _. Vlr _ n _ _ l§t _ iF _ ASA ki e ntit _ 4rod T e r . hn _ l Infml _ atlon F _ tlity , P. O , Box 33 , _l iegePm k, P q D _ 7 _ 0 i .......... i ° , , t S U lkilY A b rie f wi nd -t unnel / flig h t da t a c orrela ti on for th e B o ei n g 737- 1 0 0 airplane has been m ade. The _ tnd-tunnel data w ere publ i shed i n N A S . _ TN D - 59 7 1. Th e resu l ts s ho w ed excellen t a g ree m en t be tw een wi nd-t a_ ,n e l and flig ht tr i m med drag polars at Ma t h n u mbers less th a n 0 .6 7 . Th e wl 1 , _ - _i t:,-nel da t a p r edi ct ed larger drag incre m ents due to co m press i b i l t ty an d _ , _ 4 , a ll ft- c urve sl o pe about 9 pe r cent h i gher t ha n fligh t .
INTR O DUCTI O N _ Th e Nat i onal Ae ro nau ti cs and Space Adm i n i s t ra ti on and t h e Boeing : C o mpany conduc t ed a c oop e ra t i ve wln d -tunn e l / fl igh t data c or r elat i on program f or the Boe i ng 737 -1 00 tran s p o rt airplane dur i n g Ja n u a ry 19 6 8. T he 737 a l rp l ane i s a twln-turb o fan, sh o rt-haul, subs o n i c transp o rt c a pa b l e o f c a rry i n g ab o u t i00 passenge r s. Th e resu l ts o f t he w l nd-tunne l st u dy c o nduc t ed in t he Lan g ley 16 -f oo t trans o nic t unnel ar e pres e nted i n refer e nce i. A "" c o r r e l at lo n o f this wlnd-tunn e l da t a with t h e _l i g ht data supp l ied a t t h at t ime ., b y t he B o eing C o mp a ny w a s ma de b ut n ot pu b lished bec a u s e a n adequate a naly s is to a ccoun t f or t he known differences b etween t he ai rp la ne a nd w in d- t unnel = : m odel w a s not ma de. In 197 3, the Lan g ley Re s earch Ce nt er p u rc has ed a Bo e i n g 7 3 7 - 1 00 airplane in o rder to c ovlu ct a varie ty of fli g ht res earc h pr o gr am s in c luding wi nd tunn e l / f llgh t c o rre l ati ons . Bec aus e o f th i q r ece n t ac qu ± s it lon , i t n ow b ec om e _ a ppropri a te to doc um en t t h e b r i ef w l n d -t un . , ,l : 'f l ight data : co c rel ati o n r ae nti o n ed a bove.
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": SYMBOLS _ r ¢. !
--_i ' ; M odel f orces and mo m en t s w ere referred t o a stability a xis s y st em w i t h ,', t he model m o me n t reference center loca t ed 82.80 centime t ers r earward of t he J,.;1 :_ , :_ , model nose correspondin g t o 22. 4 percent of the w i ng mea n aer o dynam i c ch o rd ,_ ., _, _ 'h t ch w as approximately a t the nom i nal center-o f -gr a v i ty p o s i tion of the :'i'i._i:._ . , a i rplane. ._ " :g;i:i A aspect rat i o _" : _ A wetted area - ,_,_ , . W _: ' , b span : .... _ w i n g m ean ae r odynam i_ c cho r d _- : '!_;_," CD drag coe f_ : _ c l en t , _ , '_, qS ;_:':': ,, _ : , , _ ( CD, f )F computed fl igh t s kl n-fr l c tl on drag coeffic i e nt - : ;g£! : (C ) average computed f l i gh t sk l n- frl c tl on drag coef f£ c i en' : D, f F,av :!"! " (CD, f) computed wl nd- t unnel skln-fr l ctlon drag coeff ic ie r. t .
- :;:i CD,tri m trim drag coeff i c i en t , : _,; : CL l i f t coefficien t , Lift qs _ :% .,, • . ._.. , i CL, t rim tr im l i f t coe ff ic i ent ",i: , . ,: : , CL _ llft-curve slope p e r d e gr e e '_ii' , A CD,f (C D ,f) N .T. - (C D ,f) F ,av • !
_. s . % , ACD , M dra g -coefficient i ncremen t due to compressibility [c . ].. o.,, H alt it u de Lre f reference length M free-streamM ach nu m be r - May average free- ft rea m F _ ch nu m b e r Pm free-s t rea m s _ at i c pressure q free-str eam dyn ami c pressure R Reynolds number based on c Ray ave r a g e Reyno l ds n um ber Re yn o l ds number per meter S wi n g reference are a T t s tagnat i on te m p e rature "' W a ir p l an e mass 6 st ati c-pressure corre c t i on p a r a meter for correct i on t o s t and a rd se a -level conditions (p _ / 101 325 ) 6 h incidence a ngle of horizont a l t a il, pos i t i ve w hen tr ai l i ng edge is do w n MODEL _ 4D AI R" LANE A s k etch of the 737 a irp la ne is shown in figure I. T h e a lrp lan_ i s a twln-turbof a n, short-h a ul, subsoni c t r a nsport w_ Igh i n g a bo u t 4 5 0 00 kil o gr am s , capable of c a rrying about l O0 p a ssengers a t a c ruise M a ch numb_ ,r b e t ween 0.7 8 and 0. 80 .
/ I _ i I " :. ' I , i...... : + , , C o mplet e d et a i ls of t h e O.062 -sca l e m odel ca n be f o und i,_.,., , ,..' , , I .
Th e m oJe l -co mp one nt des i gna t i on of r eference 1 will a l so he , : , .d : m_ , f or th i s c orre lati on , d ata f or conf i gur ati on BW 1 H V N 1 T will be p r ese_lc d, i ' h o t ogr a ph s o f t he wi nd-tun n e l mo de l a r e g i ven in figur e 2 .
The fo ll o wi n g kno w n d iff erences e x ist ed be tw een t lk . m, , d, I _ tn ! ai rp lam .
T he ai r pl ane ha d o p e n lan d i ng ge a r w el l s, that i s,t here w et , . no p.,n_.i s ., ' co v er i ng t he la nd i n g g e a r. T h e m ode l fus e lag e was c o n stru ct ed . _i_i. a ._. ' . o ot L ,"_ , un d er si de a nd no a t te m pt w a s m a d e to simul ate th e o pe n landing , . . .,i+ _ . :; ,. . cht.
ge ar in it. An a uxilia ry pow er unit e xh a ust lo cated at t h e e n d o f the a_ r - : p l a ne fusel ag e w as n ot s imula ted. Fo r th e wi nd-tu nn e l mod e l , the na c e ,_i, ;= i n l e t ve lo c i ty r a t io wa s nm t ched to t he ai r pla ne. A s n r esul t, the t_,o&e_ n a ce ll e ex i t a re a wa s la rger th an t he equ ival ent sc al ed a t r p lat_c no z z. _ , ar e a . Bec a use o f t h is di ffe r enc e in n acelle exit a re a , the m o del nat. - ; :c o O _ . a f t er bo d v b oattail a ng l e was 7 w h ere a s t he ai rpl an e boattall an g l e _;,as _d.9.
No allow a n ce was ma de on t h e wl nd -t u n ne l mo d el for win g t wis t d u e t o @ a e roelastic e ff ec ts. T h e wing twist u n der fl :.gh t c o nd itions was e st_ : . a : : ': by O Boe i ng to b e I t o 1.5 .
.' AD J UST M ENT S T O D A T A ! Th e wlnd-t u nn e l d a t a of re f e r e n ce 1 have b ee n a d j usted f o r n ac elle t i n ter n a l a xl a l fo rce a n d s up port in t er f er e n c e e f fect s . No o t her adju_tr.: c +t t . _ w ere ma de to these da t a . T he wln d -tunn e l trimm ed d ra g pola rs f rom r , _-fert, t_ c c _ 1 , ( fi gure 17 (d )) ar e p re s en te d h ere in a s fi gure 3 .
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" ' _+' , + : +, ,_ I I ++ +; F , ' , ........ I ' + ' + 'i?i ' -- _'r ' _ Fli gh t te st resu l ts we r e suppl i ed b y the Boein g Comp a ny . Thc:i e f lig ht d ata a s supp li ed we re reduced w i t h a reference area of O _ 49m 2 mo de l, s cale.
.'., These re s ul ts w er e t hen a djus t ed to the wi nd t unnel reference area of _ : :' 0.36 7m 2 . A t r ai l i ng co n e w as u se d t o deter mi ne ai rp l ane K, ch numbe r . A ,ii" _":_ dr a g co effi c i e _; o f 0 . 000 3 (mea s ur ed w ith "fis h sc ale" ty pe b alance) wan : ? : .... " sub t r a cte d fro;: L he flig h t d r a g , -o e ffi c i en ts t o acco un t f or t h e dr ag o f t he .x ' ,., j),;:, tr ailing co ne . T he s e dr ag c o ef fi c ients a l ong wi t h ot her p er tin e n t f lig ht _,_ - ,;. i'll :}},+. m e a sure m ent s and cond iti on s a r t + l,r ese nt ed i n T a ble I.
- _): : S k in- f ri ctlon dra g c oeff i c i e nts w ere co mput ed at wi nd t u n ne l an d f li gh t , ,+ , . co n d iti o ns usi ng the m e t ho d o _ t, : fer e nce2. In f o r m at i on re qui red for the s e :- ,_,.
i!i : i : co m p u t a t ions ar e p rese nt ed i n Ta bl e s I to III . The fligh t d r a g coeff i c i en t s • . ( _t_ _.
__ :: . h av e been a djusted to the av e r age skin - fr i ctio n drag coeffic i en t ( Tab le I ) !i:ii + an d ar e a l so pre s e n ted in T a b l_ l, an d in fi gu re 4 (i d enti f l ed wit h symb ol s).
.L,,,, . +_ _ , :,: A ve ra ge fli gh t sk ln -f r i ct io n d_a,_: c o eff ici e nt s ( T a bl e I) w e r e pl otted v ersus x_ y +v . +,,+ : _, i . 7 C+_ ,: "., : - ;:_;_2'_ Mach nu mb er and v alues o f (CD ,f)F,av wer e r e ad of f the p l ot at+t h e Ma th • . _t_ • w ; .
: ._t: nu mb e r s a t wh i ch w in d t unn e l d , , ta we re o bt a in e d. Th e d if fere n ce b etween !-++%+ th e win d t u nn e l ._kin-f r i c t++ drag c o e f fi c i_r:rand th ese valu e s was then ?_! . ++? sub tr ac t ed from the wi nd - t u nne l d r_ g p olars. Thi s incre m e nt al s k i n-fr l c t l o n : ":" dr a g coe ffi cien t is also p re s e nt c d i_+ T a b le It_ .
j v _ _ : ,: . _'. A n adju stme nt is ma de to t h e skin-f r l c tlon dr ag c o ef f icien ts t o accou n t + :: fo r thick n e ss ef fe c ts (ref. 3 ) t, i ng a form f a c to r o f 1. 1 8 fo r the e ntire ii:i_i; conf i g u r at io n (ref. 1 ). Th is adiustme n t i ncr _m e s t he A CD , f i ncr e me n t s of :_' T a ble III by 0 . 0009 . A val ue f o r c x cr e_ cenc e + , rro u ghne ss d ra g c oe f f i ci e n t ++.+.;. (r e f. 3) o f 0. 00 18 wa s ob tai ned fro m th e Bo ein g Company a nd has also been ,_: _ add e d to t he tr i mm ed w ind- t u nn e l dr a g p o la rs . T h e s e fi na l adju s ted tr i m me d i_, " /. :; : ., 5 _'t I'," : .... s " + + + , .... • + " ++ . - • .+ _+_+. • .. • .. y ._ ..... • , , . . .... ,.- .... "_+ ' "+ ' :..... +'i' ) _ .+++ '_ ++-X ,, +, '" + ' :-,. - -- _. : . :., +° "++ +++ \. .....;::,._+ + .: + , + - .... , ++_.-+ ++ ' ,+ : X ............... "_. : -- .... _+ .. ",++ ,. r- . : + . ,,'+ : '_':+:+:_+,_ ,. := : '_++,_ - + - _ .....
wi nd-tunne l drag p olar s (adju s ted for a k i n-fr i ct i on , th ickn ess _, ,.d roughness e f ; e c t s) are pr es ented i n fi gure 4 by th e da sh t. d l in,, . _: .
SUHHA R Y O F R ES U L T S C om par iso n s o f adjusted win d tunne l am l a djusted fligh t dra g p o l a rs a r e pres e n t ed i n f i gure 4 . There is excellent a gree m e n t at M - 0 . 596 a nd 0.6 7 2 . Ho w ever , th ere a re l a rger difference s b et w een th e ad justed w ! _d- _ , _ t unne l and fli g ht dra g po l a rs at th e hig her H a t h nu m ber s .
A c om par ison o f fl ight an d wl nd- tun ne l co m press i bil it y dr a g zi sa ch ar a cte ri s ti cs i s presented i n f ig ure 5. The w l nd-t u nnel d_ . ta _l_ows_h_ dra g r is e to o cc u r ea r l i er th a n th e flight da t a a n d a l s o pr edi c ts la rg e r dra g in cre m en ts du e to c omp ress lbillty e f fect s .
A c omp a rison o f f light a nd wln d- tunn e l (f igur e 1 7 ( a) , r ef . I) ll f t - c ur ve slo pe s is giv e n in f igu re 6 . Th e wind-t u nn e l l if t- c u r v e slopes a re a bout 9 p erc ent high er _h a n fl ight de t er min ed val u e s .
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: _. L+ =*+ I ii! :i R EF ER EN CES • .:: , ' } J I I. C ap one , Fr a ncis J. : Long l tudln a l Aerody n a mi c C h, , r a ct er ls tlc s of a i T e I u -Turbofan Subsonic Transport Wit h N acelle s M oun t ed Und e r t he _j Wing s . NA S A l q_ D-5 97 1, 1 97 0 .
+!: 2. S o mm er , Si mo n C. ; and S ho rt, Barbara J . : F ree- F l lg h t Me a s ure me n ts of
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+_',>.,_ Tu r bu l en t- Bou m da r y-Layer Sk i n Y ri ct io n in t h e Presence of Severe ._, . _ i_!i A er o dyn ami c He a t i ng a t M a th N. mbe r s F r om 2.8 t o 7 .0.
._ ' i : N A C A ' 1_ - 3391 , 1955 .
+:_ 5 . Br own, C il nton E. ; an d C h ert, Chu a n F a ng: A n A n a lys l s of Pe r for ma nce Z _'' _ Est i ma ti o n Meth o ds f o r Aircr a f t . NASA C R -92 1 , 1967 .
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