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i : _ : NASA__Tcchni c alMemorandum 8181 7
I ; ° : L , 'i: , ( g AS,_-T M -818 _ ?) E X PLORATO R Y PIL O TED NS0- 28370 SIM ULATOR STU D E O F TH E E FF E C' _ S OF W INGLETS ' O_ H A NDLING Q f lALITI E S OF A R E P R E SENTAT I V E A GRICOLT U R A L AI R PL A NE { N _ SA) _ p Un c l as t ic JtO3 / M F I L 01 CSCL 01C G3 / 08 28178 I .
EXPLORATORYPILOTED SIHUL A TOR STUDY O F THE EFFECTS O F WINGI - ETS ON HANDL I NG . Q U A LITIES O F A REPRESENTATIVE AGRICULTUR A L AIRPLANE HARILYN E, OGBURNAND PHILIP W0 BR O WN APRIL 1980 t National A _ ro h aut l cs a n d I SOace A cl m i ntstrat i on Haml_ on , Virg l t _i a 23665 EXPLORATORY-P _ LOTED SI M ULAT _ )R STUDY ; O F THEEFFECTS OF WI NGLET S ONHANDL I NG QUAL I TZES OFA REPR E SENTA TI VE AGR I CULTURAL A I RPLAN E I _r tl y n E, " Ogbu r n a nd Ph111p1 4 . B r own .....................
L a ng.l e yR esear chCent e r SUmLAR _ An exp l orator y p t lo t ed S l mula t o _ stud y has been conducted i n ord e r to evalua t e th e effects on h a ndling qual i ties of addtngwtngle t s t o a .
representative a gricultural atrcr a f t configu r a t ion du H ng swath- r un m a neuvering. The aerod y n a mtc dat a u s ed tn t he St l,ula t{ on w e r e b asedon low-speedwind-tunnel tests o f a full-sc a le atr plane and a .subscale model. The stmul U . i on was_conduc t e d on t he L a ngle y G e ner a l Purp os e S1m u l at o r .
The _ es u lts of t h _ Inves t ig a tion showed t h a t _f o _ t he task ev a lu at ed, t he lat er a l-di r ec t iona l flandltng qu a li t i e s o f t h e a trp la ne were grea tly affected b y t he a pp l ic at ion o f wtng l e t s a nd wtng l e t c ant a ng l e. T h e a trp la ne wl t h wtng l e t s c a n t ed ou t 20o exhibi ted Sev e re ly d egraded l a t er al -d i rection al h a ndltng qu a lities tn c omp a rison t o the b a stc a i r pl a ne.
E xcessivedth e d ra l effect producedb y th e r inglet s con t ribu t ed to the un sa ti sfa c tor y l a t e r a l-directional beh a vtor o f the a irpl a ne. W hen the - _ wtnglet s were c a nt e d tnw a rd 10°, t h e dth e d ral e ff _ ctw a s r e du c ed a nd t t i ; i' i t he f l y lng q u al iti esof t h _ con fi gu r a ti o n w e r e m a r kedl y im p r ovedOve e t hos e of th e wi ngl et-c a n ted- ou t c o nfi g ur a ti o n. A lso , the cante d -in !ii wi ngl et c on fi gu ra t l o b e x h i b it edb etter han dl ing character i s- tic s t han t he b a si c con fi gu ra t i o n wi t hout w_ ng l e t s ,indicatin g that pr op er tail o ringof the wl n glet de s ign m a y aff o rd a p o tenti a lben e fit in t he are a of handl i ng qual itie s . Due to t he l imited sco pe_ o f . t h i s.
inve s tig a ti o n, h o wever,m o re research is n eede d i n o t h er area s o f the f l ig h t en vel op ebef o re s p e cific rec o mmen d ati o ns o n the use o f winglet s f o r agric ul t u r a l a ircraft ca n be ma de .
INTRODUCTION Rec e nt resear c h by t he Nati o n a lAerona u ticsa n d Space Administrati o n O n agric u lt u ral a ircraftha s incl u dedan inve s tigati o n o f the eff e ct s of i( v ari ous wing ti p m o di f ication s on t h e characteristic s o f wing ti p v o rtex
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!i!i f lo w a nd t he in ter a cti on o f such f lo w s with p articles d i sbu r s e d f J : o m_t J _ aircraft. In t he s w a th ru n , the s tr ong v o rtex f lo _, fiel d at t h e wi n g ti p o f a heavily lo a d e d aircraft C a n h av e a pre do minanteffect o n Swath w_ d th and u n if o rmity o f de p os it, In so me a erial a p p l lcati o ns, the entrainm e nt o f sm all chemic a l d ro pl et s In th e v o rtex f lo w fie ld can l e ad t o se H o u s d rift p r obl ems,wit h l ar g e l oss e s i n e ffi c i e nc yo f op erati on an d p r odu ctivity. T he po ssibi l lty o f se ri ou senvi ron ment al d a mag e ad j a c e n tt o the w o rking a re a is ano ther s eri ousp r o blemw hen d rift o cc u r s . Resg l ts ob t a ine d fr o m te s t s in t h e Lan gl eyV o rtex R e sea rc h Fa c i l ity ( r e fer e nce 1 ) have s h o w n that t he use o f wt ngle t s o n a g ric ul - t u ra l air c r a ft m a y re du c e t h i s d rif t p r oble m b y d iff us i ng th e wi ng- tlp !i_ .........
J alm r_ vortex and rai Sing i t to a highe r pos i tion r el a ti ve to the w ing- m oun t ed sp r a y boom. Thes e potential bene f ic ia l effects o f_ t _ gle t s w e r e shown to be rel a tivel y Insens it ive tO ch a n ge s i n w tnglet c a n t a ngle, i n t h e r a nge between200 canted ou t a nd I0o c a h t ed i n.
On t he basis o f these p r o mi s i n g r esu lt s , a se r ies o f w i nd- t unnel te s ts o f a f u ll-sc a le air c raf t a nd a s m all- s c a le model w ere pe rf o rme d, in o r de r to de t erm i ne th e a e r od yn am t ,c pe rf o r m a nce, Stability , a n d co n tr o l :: _ ch a r acte ri st i cs o f a r ep r esent a t i ve ag ri cultu r a l at r ptane_ wt th wf nglets.
The wi nd - t unnel d a ta f o r the a ir c raftwt th wi ng l ets ( r e f e r ence 2) sho w ed moderatelevels o f improvedp . _r fo rma nce onl y a t high li ft c oe ff ic i en t s_ a s would be expected (re f ere n ce 3). However, t he me asuredst a b i l ity and con t rol data indica t e d a po t ent i a ll y seve r e degrada ti on in t he la t era l - d ir ec ti o nal hand li a g qua liti es o f t he a i rc r af t wit h wi ng l ets, due p _ P _ Jm rtly t o a l a r ge in c r ease in th e l a t e r a l s tability d eri v ativ e ; (d i h e dra l e ff ect).
An exp l o rat or y p il o t ed s im u la t i o n s t ud y w as t he r e f o r e co n duc t ed in o r de r t o de t ert, t ne t he seve rity o f t he de tri men ta l e f fec t s of wt ng l e t s on the l ate r a l -d 4 rec tt ona l hand li ng qu a li t i es of t he a i rc r aft a nd to d e v elop po tent i al solut i o ns t o an y p r ob l e m s. The study w a s conductedon the L a ngley Gene r al PurposeS i mul a t o r , and a ptlot i ng task wa s des i gned tO e valua t e the effect o f w tngle t s o n hand l ing qual i t i es du ri ng r ep r e- sentative s w ath - run maneuve r in g . The ae r od y namicd a ta used tn t he sim u l at io n were bas e do n t he r esults o f lo w -speed w i n d- t u n nel tests of t he f ull-scal e ai r cr a ft and of a l / lO-scale modelof t he con f igu r at i on. ( ,. - u-, ............
. i'_ t i _' SY N BOL S ti A ll ae r odyna mi cd ata a nd f l igh t m o t io n s are r efe r enced tO the body sys t e m o f axes shown tn f i gure 1. The u n tts f o r phys t c a l q u an titi es i_ used he r e i n a r e p r esented i n t he In t e r n a ti onal Systemo f Un it s (S I ) a nd _!_ U.S. C u s t om a r yU nit s. The m e a su r e m ents a n d c a lc utatt ons we r e m a de in i t he U.S. C us t o m a r yUn its . Conve r s i o n f a cto r s f o r the tw o sys t e m s a r e i g i ven in r e f e r e nce 4.
/' a_ n o rm a l a ccele rat ion, positiv e along nega t ive Z b o d y a xis, g un it s (l g = 9.8 m / sec 2) ay l a t e r a l a cce l e r a tl on, po siti ve al ongpos itiv e Y b Ody axis , g units b wing S p an,m (ft) ! I C D d r ag c oe ffici en t , Aerodynamic dr aq f orce _. , CD , t t o tal d r a gcoe ffici e nt i C L llftc oe ffi c i e nt , Ae _..._ d _ n a ni! c llftforce C L , t totalliftc o effici e nt • cl _o ll l ng -m o m e nt coe f f l cle nt abou t X b od y a xi s, Aerodynamic rollln) moment Cl , t totalrol l ln g-mo m e nt co e fflcl e nt C m pltchln g-m o me nt co e ffici e nt ab ou t Y bodyaxi s, A e r odyn amic _Itchlng moment °_) ii , ¢ m ,t t ota l pit c hing- mo men t coeff i c i en t C n yaw tng- _m len t coe ff t c t e nt about Z bod y axts, Ae ro d_na_t c _awlngmon_nt q S b Cn,t t o t a l y awtng- m o m n t c oe ff icien t C T thrust coe ff tc t en t ,'T / p n2D 4 C X X --axts f orce coef f ic i en t a lo ng pos itiv e X bod y a x i s, Aerod_namt_ X-axts force CX,1; _ _ t o tal X-ax i s force coe ffi c i en t C y Y- a x i s force coeff i c i en t along pos iti ve Y body a x i s, Aerodynamic Y-axts force Cy, t t o t al Y-ax i s force coeff i c i en t C z Z- a xt _ f o r ce coeff i cien t a lo n g pos tt tve Z bod y a xts, Ae ro dynamic Z-axis force
i s
CZ,t t o ta l Z-ax i s fo r ce coe ff icien t wi ng meanaerod y na m ic.cho r d, m _ f t ) D prope ll e r d i a m e t er , f t .
g a cce l e rat ion du e t o g ra v ity , m l sec2 {ft / sec _ ) h a lt itude, m (ft) i I x, I y, I z momen t s o f tne rt t a about X , Y, and Z bod y axes, kg- m 2 _ s l ug-ft Z J I XZ product O f tne rt t a w t t h r espec t t o X and Z bod y axes, kg. m Z (slug.f t 2) : m at rplane mass, kg ( s lu gs) n prope ll e r r ot at ion al speed, _ ev . d i, :: p pe r tod, sec _ p a ir p l ane r o l l r a ts abou t X bodyax i s, deg / sec or Pad / _ sec _ : _ a ir p l ane rol l acce l era ti on abou t X bod y ax t s, deg / sec 2 ' o _ r ad / sec2 : _! , ) q ai r p l ane p it ch ra t e a b ou t Y b od y a xi s, deg / sec o r _i :: rad / sec " : , _ a t rplane pi t ch accele r at i on a bout Y bodyax i s, deg / sec 2 o r r a d / sec2 f ree - stre a nt d y nam t cp r essure, N / m 2 { lb / ft 2) r y a w r a t e abou t Z b od y ax i s , deg / sec o r r ad / sec )i _ y a w accele r a ti o n a b out Z bod y ax i s , d eg / sec2 o r r ad / sec 2 S w i n g a rea, m 2 ( f t 2 ) T to t a l i ns t an t a neous eng in e thru s t, N ( l b) t ttme, sec J tl / 2 t i me tO d e .rap t o one-half ampl i tude, sec r 0_ ,v, w compone n ts of a t_l ane ve l oc t t y a l ong X, Y, a nd Z bod y axes, m / sec ( f t / sec) u ,v,w a trpl a ne a cCelera ti On along X, Y, and Z bo dy a xeS, . m / sec 2 ( f t / Sec 2) V a ir p l ane r esu l ta n t ve l oci ty , m / see ( ft / sec) X,Y,Z a t_ plane bod y axes (s _ e fi g u re 1) !i , _ angle of attack, deg .... _ S angle of sides lip , deg M 6 a a tleron _f iectt o n, po s it i v e M r le f t _ 11, de g 8 e elev a tor deflec t ion, post t tve Mr pi t ch n ose-d _ n , de g 6 r _ dderdefle c t ton, postttve _r l e f tyaw, deg 6 T th r ot t le p o sition , fra ction of maxi m u m v a lue 6 w. _ nglet cant a ngle f _ m ve rt ic a l, positive for outw a r d c a nt, deg [ d a mp i ng ratio p a_0 s pherlcd e n s l_, _ / m 3 (slug s / ft 3) ® ,¢ bl er a n g l es, d e g ti me co n s t a nt , sec C L ._ _ CL = _C_ = _C t = _Ct = _C t l e 3 . ___ e C, p _ Cir _ CiB __ _ Ct6 a __a . B O x ) C _ . _ . . m C m = 3C m • = 3C n = ) Cn Cn ) , _ C n = I C n C n = )C n = BC y Cy = 8C y Subs cr ip t s: DR . . dutch r ol l mode m ge tnc _ emen t tn va r ia b le produced by groundeffect R roll mode S s p tral m odO _ e i n cr eme nt tn va r iable p rod u c edb y elevator de fl ec t io n o Abbr e via t io n s: t LCDF lateral co n t r ol dive r gence parameter I / r p m re volu ti ons pe r m t n u t e f or engtne -o . _' _ . " • _ : o _o _ .... o . _ °' _ ' _ _ . ......................... o " ¸_i_ _ ' : _ :. _ , , . o o _ < . " )_) , , o a VFR vt s ual f ligh t rules VL DS vtsual l a nding d i spl a y system DE S CR I PT I ON O F A I RPL A NE . A t h r ee - v l ew ske t cho f th e si mul a t ed alr p l_ne co nfi g uration , show i ng t h e _ wln g _ e tconfi g ur a tion s e val u at e d , I s pre s ent e d in _ figur e 2 , a nd th em a ssand g eo me trlc c h aract e ri s tic s use din th e simulation a r e li s t e d in tableI. Th e ou_ardly - ca_wlngl e t d es ign(8 w = 20°) wa s fir s t "propo s ed for th e -alrcraftJn a n att e m p t to mini m i z ethewak e vo_ro - blemdl s cu_d_rll e r. A s e cond wlngl e tcantangle , 6w = - I0 °, wa s also e valuat e d aft e r - analy s i s Indlc a _ e d p_Itl a lly d e graded lat e ral - dir e cti o nal handlin g qu aliti es for the configuration withcant e d - o u t wlnglet s .A s di scussed i n r efe r ence 2, the wt ngle t p l an f om and s t z e w ere n o t op ti m i zed f or t h f s app lf ca tt o n ; ho w eve r , gu i de li nes g i ven i n r e f e r ence 5 w e r e used t o deve l op the con ff gu ratt on tes t ed.
Conven ti on a l a e r od y nam i ccont rol s w e r e sim u la ted i nc l ud i ng conven - ti on a l e l evato r s f o r p it ch con tr o l , de fl ec tf on O f wf ng - m ounted ail e r ons .....
f o r r o ll co nt ro l , an d rudder de fl e cti on f o r y a w con t ro l. S tatic ae r o - d y nam i cda t a used i n t he sim u l a ti on w e r e ob t a i ned f ro m C he r esu lts of reference 2, d y na mi cde ri va ti ves w e r e es timat ed us i ng the methods of reference 6, a n d t he effec t s of the propel l e r s lt p s t re am w ere n eg l ec t ed f or t h i s exp l ora t o w s t ud y . The e f fect _F ground proximity o n the ae ro - d y nam i cda t a w a s a l so es ti mated .
A l l s i mu l a ted f li ghts w e r e m a de f or a cent er - o f-g r a v ity l oc a t t o l Of 0.30c , w h i ch i s r epresen ta t i ve of an a ft c.g . pos iti on f o r the s im u l ated atr pla , e.
, d DESCR I PT I ON OFS IM ULATOR Coc k p i tandAssoc i a t edEqu i pmen t A v i e w o f t he cockp it o f t he Gene r alPu r pose F i xed - B as e S im ul a t o r ts sho w n i n fi gu r e 3. Fo r ce - f ee l cha r ac t e ri s t ics f o r t he con tr ol s ti ck a nd r udde r pedal s a r e si m ula t edb y a P , o gr a m ableh y d r a ulic se r vos y stem.
Th r o tt le con trol s f o r .. t h t s study w e r e loc a t ed on t he le ft s i de o f t h _ cockp i t. A v trt u a l im ag e colo _ vtsu a l d is pl a y wa sp r ov i ded f o r t he p t lo ti ng task. A sound s y stem w a sused t o p r ovtde_ a u _ l cues r el att ve t o eng i ne r p m a nda ir speed, _ V i su a l D i spl a y Thevt s ual d i spla y u tt l i zed t he L a ngle y Visu a l L a ndtng D i sp l a y S ySte m (VLDS), w h t cht s displ ay edIn colo r t o t he p f lo t t h r ough a r e- fra c t ive vt rt ual image c ) lo r dt _ pl a y sc r een. TheVLD$ts a _ a me r a/ model s y s t em w h t chgene r a ies a v i su a l ou t - t he - w t u do w scene f o r t he ptlo t o f t he s i m ula t eda ir c r a ft . TheVLDS s y s t emcons i s t s o f a 1 8.3 m - b y - 7.3 m (60 f oot-b y - 24 f oo t ) dual . scaled t e rr a t n m odel,a l _m pbank t o ill u mi na t e t h e m ode l, a t h r ee deg r ee - o f - fr eedom tr ansla ti on s ystemt o pos iti o n t he ca m e r a,and a _th r ee deg r e e - o f - fr eedom op ti cal / r o t a ti onal system m a t ed t o a colo r t elevis i on c am e r a. TheVLDS p r ov i de s non - co m po sit e t e l _ - v t s _ Ons t gna l s t o a n ex t e r nal Stm ula t o _ cockpi t wi ndo w d i spla y d e v i ce t o p r ov i de a fi e ld o f v tew o f 48 deg r eesho ri zon t all y and3 6 d e g r ee s ve rti call y . Th e op ti cal / r o t a ti onal System also e m p loy s a " sky pla t e" op tt cal dev i ce to c re a t e t he s ky above t he t e rr a i n scenean d to p r ov i de for 11mt te d v4 stbtlt ty condi t ions. Addi ti o n a l de ta t l s pe rta ining t o t he VLDS and t he gehe ra l pu r po s e stmui at o rar e given in r eferences7 a nd8.
Compu t e r P r ogP am and Equip m en t T he- _e ne r a l purpose fi xed- b a se si m ul at o r i s d r tven by a r e a l- t i m e d t gt t al si m ul a ti on sys t em a nd a Con tr ol Dat a C y be r 175 computer. The dyna mi csof t he ev a lu at ion ai r p l ane w e r e ca lcula t ed by using equ a ti ons o f mo ti on wit h a f ixed-In t e r v a l (1 / 32 s ec) nu m e ri c a l tn t eg r a, tt on t ech- n i que. T he equ a ti ons us e d ae r odyna mi cd a ta a s a f unc ti on o f a f a t abu l a r f o rm. Theseda t a w e re de ri ve dfr om r esul t s o f I o w_ - .sp eed static _ z f o r c et e stsof t he full-scal e a !rcreft a nd a one -ten th _ca_mod e l, | whic h wereconducted a.t Lan g ley(refere n ce 2 .). T he datainclud e d an angle- o f-att a ck r a n g efrom0 ° t o 2 0 ° , and all o f the aer o dyn a mic data pre s e n ted hereinare re p re s entative o f, a t h r us tcoefficient (CT)__of 0.14.
The equati on s o f m o ti o nu s edare givenin appendix A.
EVALUAT ION P R OCED UR E S . The r esu lt so ft h ei nves tigati o n w e r e ba sed o n p il o tc o mm en ts a n _ t ime - h.ist_rec o r d s o f a ir pl a ne m o tlo ns , co ntr ols , a n d the air p lane f..1.tght path o ver the ground f o r the v a ri o u s maneuvers I_erf o _ed. The Coo er- H arp e r handl i n g q u a l itie s r a ting sc al e (fi gu r e 41 an d p ilot _: c o mm en t s w e r e u sed t o ev a lua t e eachconf i gu r a ti o n f lo w n (r e f e r e n c e g) , _; : M os t o f t he ev a lu a ti ons w e r e pe rf o rme d b y a NASAr ese a r ch te s t p i lo tw ho , had r e c en tly c o m p l e te d trainin g at an ag ricultural a lrc_ a ft p i lo t school - ' . and had l imit ed pi lo ti ng ex _ e rl ence i n seve ra l d iff e r en t a g ri cul t u r a l : " aircr a ft.
Y, 1 0 _%; .. '. . _, _ _ -. . - . . _ • , J T a sk P e scrtpttoh A sketch whtch desc r ibes the ptlottng t a sk usedto ev a lu a te th e h an dltng qu a li t ies o f t he a i rc raf t ts sho wn tn f tgu r e 5. The t a sk w a s . destgnedto test the h a ndltng qu a lities o f the a t r c raf t tn a m a nne _ wht c h would be a pplic a ble to a r e a lis t ic a t r c raf t r equi r e m en t . I n t hts case, the s t r a ight f or w a r d task o f m a i nt a ini ng wt n gs level al ong a Str atght t r a ck i n st mul a tto &_f t he unobs tr uc t e d swat h _ un w a s s u f _ftc i en t t o reve a l t h e r el a ttve handl i ng qu a lit i es o f t he con fi gu ra - t i ons s t ud i ed.
T he sect t_ n o f t he VLDS t e rra in dtspl ay used f o r t he t a sk (f tgu r e 6 ) t n cludes one wt de r un waya nd it s a ssoci a ted p ara llel tax tw ay . Th _ ta xl w ay aente r line w a s the r e f e r ence tra c k . L i ght i ng o f t he VLD $ p r o- vtded a d ay VFRsceflewtth vi si b i li ty o f a t le a s t 5 m tles. The t as k beg a nwtth the a t r cr aft pos i tioned 610 m e t e r s ( 2,000 f t ) f ro m the run w a y edgeat an a lt _ ude of 4 6 m e t e r s (150 ft ) a nd t rtm led f o r st rai gh t a nd level f ltg h t at 54 m / sec ( 120 m p _ ). The p t3 o t was r equt r ed t o a pp r o a ch the- _ unw ay , dtve down, a fld f ly the c o m ple t e length o f th e r u nway dt r ec t l y abovethe _ en t e r l_tne , wit h f_ _ xed th r ottle pos l tto,,, a t low altttude (about 3 meters). L a te ra l t ra ck co rr ections were madeby wings-lev e l sideslips w h ± chgene ra t e d a s t de f oPce, a ccele r a t i n g the atr plane b a ck to w a r d the cen t erltne. Ptlot loo p closu r e on late ra l t r ack e rr o r wa s madepri m aril y b y meanso f rudder tnpu t s. Atle ro ns were used tn response tO b a nk a ngle er rors whtch r esulted from the rudder tnputs. The p11ot a t t e m pted to m axt m tzel a te r al tra cktn g pe rf o m anc e whll e simult a n e ou s l y holdtng the wtng s lev e l an d s m oothl y cont r ollin g at titude. Al t houghno e xt e rn a l tsturb a n c es (such a s tu rb ul e nc e o r ran doml a t e r a l s t e p o f f se t s ) w ere s i m ula te d, enough tra ck, b a nk a nd al t i t ud e e r ro r s w e re induc e db y pi l oti n g t o cre a t e a h ig h w orkload t a sk, Onc e the at Pc raft re a ched th e f ar end o f t he r unwa y t he run w a s termin a ted. Th e next run bega n fr o m the s a me t n _ tt a l cond iti o ns; no t u rn s _ e re madeb e t w ee n runs.
Ev al ua ti on o f Handling Q u alit ies I n ev al u a t i ng the s i mu l a t ed a ir p la ne, nume r ous Puns w e r e m a de t n th e task. S u ff icie nt . flig h t s we r e m a deto ensure th a t the p t lo t 's " le ar n i ng curve " w as re a son a b l y w e l l establ i shed be f ore dr aw ing a n y co n clus t on _ r_ ev a lu ati on results . Ev al uat i on o f . h a nd l ing qu a l i t i es wa_ : _ , .'... . J ..
Cooper - Ha r pe r p i lo t r at ings a nd p il o t / veh i c l e p e rf or m a nce.
DISCUSSION OF S T ABIL I TY ANDCONTROL CHARACTERISTICS TO provtde a f ound ati on f or t he a n al y s i s a nd i n t erpre t a ti on o f t he s im ul a t i on r esu lt s w hic h f ol l o w , se l e c ted a e r o d y n a mi c s t ab ili t y a nd con t rol chara c t e r ist i c s of t he s im u l a t ed a f rcra ft conf i guration ar e presen t ed and d i scus s ed t n t his sec ti on . The a erodyna mi cdat a f o r c on d i t ions I n t he sw a th r un t ask a r e l i s t ed tn t a b l e t I , and t h e r ep r esen tati on of t hese da t a In t h e equa ti ons o f mo r to n i s d i scussed tn appendixA.
Longi t ud i n al C har a c t eris t ics The ltft cha r a c t er i s t ics o f t he simu l a t ed con f tgur atl on a s noted dup i ng wi nd - t un n e l t es t s w e r e tha t the bastc a i rcra ft exper i enced a "_l!.i b reak 4 n t he l tft c u r ve at an ang l e o f attack of a bo ut 15°, a n d ano t her
°":fl) 12
b r eak occur r ed a t htgh e r a ngles o f att a ck _ se e f tgu r e 7( a )). As : I n dica t ed by the 1 1 ft data, the a ir c r a ft expe r ience s an in c r ease tn 11ft w_t l1 _ t J 1 e addt tt O n o f w t n g l e t s. The long i tudin al s t a b 1 1 1ty of t he a lr - pl ane w as no t signi f ic a n tly changedb y t he a dd iti on o f wi ng l e t s, a s Ind i c at ed b y t he pt t ch t ng m omen t d at a ( see fi gu r e 7 {b )).
L at e ra l-D t r ec tt On al C h a r a ct _t s ti cs The s t a ti c l a t e r a l -d ir ec tiO n a l s t ab ilit y ch a r a ct e ri s ti cs fo r t he bas i c at r c r a ft a nd each o f t he tw o wJ ngle t conf i gu r a ti ons _ chn w n i n r f_ g _ e 8. F i gu r e 8( a ) sho w s t he s tati c di r ec ti ona l s t a b i l it y de ri v a ti ve, Cn _ ; f i gu r e 8(b) sho w s t he la t e r a l , s t ab J l tt y_O_ _ _e f fec tJ ve d _ hed r a l de ri v- a t ive, Ct 8 , and t he _ de- X o r ce de ri va ti ve, Cy _ , t s sho w n i n fi gu _ 8(c;, a l l as a f unc ti on o f ang l e of a tt ack. A t each angle o f a tta ck, each der 4 v at tve w as co m pu t edb a sedon a e r od y n a m i cda t a a t B = +_10 °.
The d a t a sho w tha t Cn _ r e m a i ns posJ tt ve (s t able) f o r a ll t h r ee configu r a ti ons t h r ough the r ange o f a ng l e o f _t ack used i n t he pe r fo r - manceo _ swa t h P un handl t ng qu a li ti es ev a l u a ti on t a sk. HO w eve r , so m e d eg r adati o n tn dt r ect t ona! _ htlt t y t $ Ind i cated f o _ 6w = -10° : I n co m pa r ison t o th e b as tc a ir craf t , and t hts deg r ada ti on i s m o r e pro- n ounced f o p 6 w = +200. The p l o t of C tB aga i nst _ (f 4 gu r e 8(b)) i s of pa r t i cu lar I m po rta nc e , s t nce t h is p l o t sho w sthat fo r 6 w - +20°, the w trtg l ets Inc r ea S ed t he postttve e f fec t ive dthe dr al ( -C _B ) of t he atPc r a f t b . ,;a f a cto r of about 3 fo r the ang l e - of - attack ra nge o f t h e swath run.
FoP 5 w - - 10° + t he i ncrease t n -C tB f _ the b a stc conf i gu r at i on w a s muchless than f or 6w - +200. Th tS part i cu l a r r esu lt was n o t un - expected, becauseof con s ide rati ons w h i c h a r e 411 us tra ted t n f i gu r e 9.
This fi gu r e S ho w s t he con fi gu rat io n with 8w _ 2 00 a n d tw o g e o m e tric changes wh i ch m i gh t be used t O reduce t h _ e ff ect ( re dihed ra l. One c hange iS t o s i mpl y in t roduce negat i ve geome tric d i hed r al ( a n hed ra l) in t o t h e w i ngs b y lowertng t he wt ng t i ps. Ho w eve r ,a ca l c ul ati on o f t he a mou nt o f wi ng d i hed ra l a ngle c hangerequ i red in o r de r f o r w t ng le t s wt th 6 w = +2 0 0 t o b e added w h i le ma int a i n i ng t he o r tg tna l ef f e cti ve dih ed r a l o f t he ba s i c aircraft shows t h at 12o o f w i ng anh e d r a l i s r e q u ir ed. A s ill u strat ed i n fig ure g , t h i s met ho dw ou l d re sul t i n pr o bab l _ n g tip c on tact wi t h th e_g r ounddu rin g normal , opera ti o n s an d t_ u n a cc ep t a bl e .
A no t he r w ay o f r educ in g d i hed ra l e ff e ct f o r a c on fi gu rati o n w it h wfn gle t s i s t o c an t t he _ng le t s i nw ar d. Th i s r educes t he e f fe cti ve d i hed ral b e c ause unde r side s l ip ped c on ditio ns t he f o rc e comp o ne nt no r m a l t o t he w i ngle t su rfac e wi ll b e d ir e ct ed a lo n g a l tn e w hi c h p a ssesmuch c lose r to the c en t e r o f gravity of th e aircraft.
Anoth e r s tatic derivativ e whichiS se n s itiv e to wlngl e ts and wlngl e t cantangl e- l s Cy_ , whichis pl o tted for e achwlng - tlp configuration in figur e 8(c). It is evid e ntthatt h e additi o n of the outia_ly-cant e d wlngl e ts {6 w = +20 °) to th e ba s icaircraft doubl e dth e valuesof -CyB .
T h e reis alsoa sub s tantial incr e ase in-CyB with th e wlngl e ts canted inward (_w = " I0°) " T he s ignificanc e of thi s r e sultIn t e r m sof its e ff e cton th e handling qualiti es of th e s ubj e ctaircraft Willbe describ e d in a later se ction.
T he dynamiclat e ral - dir e ctlonal s tability charact e ristics o f th e J air plane W e r e calcula t ed on th e bas i s o f th ree deg r ee - o f-fr eedo _ !
lt n eart zed l a t e r a l- d ir ect i on a l equ a ti ons a n d t he a ero d yn a m i cda t a o f 1 4 ta ble Ii . The r esul t s of th e cal c ul a ti ons f o r t he t h r ee wt ng- ti p cOhftgu r a t tons ap e presented in table II I . Data a r e shown fo r the Dutch - r o ll , s piral, an d ro ll ,l _ de s o f m o tio n f o r t he 1-g trim cond i t i on at th e c ope r at i ng speedo f the ai r c r af t f o r the s wat h r un. The da t a i ndica t e W_ t hat all t he modes are stabl e. Both t he deg ra d ati o n t n d ir ec t iona l Stab ility a s w e ll as t he i ncre a se _ n d ih ed r a l e ff e c t wit h wt ng l e ts = _ cont ri buted to a slight decrease i n Dutch r oll damp i ng. The Dutch r oll _ . damp in gis close r to t ha t _ of t he bas i c a ir c r a f t w hen t he w t ngle t s ar e ' _ , . ' c an ted inwar d 10O. Some of the R r edom t n an teffects that t he _ s t a b ili t y i l Ch ara c te rl stt cs have on t he l a t e r a l - d ir ec ti ona l con t ro l cha ra cte Pf s tt cs ii ; ii o f the a ir c r aft wf ] l be _ d tn t he f o ll o wi ng sec ti on.
_ _ _ .
_ La t e r a l-D ir ec ti on a l C on tr ol l The ex t ent of t he degrad a ti on i n h a nd li ng qual iti es o f t he a ir cra ft )_ due _ t o t he a d dtti o _ of w t ng lets co u ld no t be adequa t ely u nderstoodun ti l = a p tl o t e d evalu ati on co u ld take place. H o w eve r ,an exam 4 na tt onof so m e i m po r t a nt st a b i lit y and con tr o l pa r ame t e r s gave t he fir s t i nd i ca ti on o f : po t en ti a l p r oblema r eas. T h e la t e r al cont r ol di ve r gence pa r a m ete r (LCDP) li i s of t en used t o a p p r aise r o ll - Co n t r o l e ff e ctiv ene s s. T h i s pa r a m e t er i s !l def i ned a s: C n 6 a L C DP = Cn B - C l B t _ - - ii 6a bT ° t ; PoSi t ive Values Of this p a r am e te r in di c a te no rma l Poll resp o nse ( i . e ., r tgh t Poll cont r ol r esults tn a r ig ht r oll). W hen t he LCDP i s near ze r o, fii_ the r oll r esponse ts w e ak a nd Oscill a to r y , a hd heg atl Ve v a lues i n d ic at e ) i! ................................ .....
revers e d response. W he n reVersed re spons e i s encoun t e r ed, a r igh t r oll cont r ol i npu t r esults tn a le ft r oll ( i. e ., r oll r eve r s a l). Lo w v a lues of L CD P c a n r e s ul t w henthe e f fec t ive dihed ra l ( - Cl B ) is l ar g e a nd a dve r s e yaw f rom a tl er on deflec t ion (C n _ > O) is pr ese n t . T he d ata o f f i gu r e 10 sho wthat t he bas i c airc r aft has pos itiv e values o f L C D P f or t h e sw a t h r u n a nd w ou ld t herefore be exp e c t ed t o have sa ti s f ac t or y l eve l s o f proper r o l l r esponse wit h a il e r on def l ec t( o n . The a ir cra ft wit h wt ng l e t s c a n t ed i n w a r d, 6w = - 10°, w ou l d a l so be exp e c t ed t o exh i b it p _ ope r , t houghsome w h a t w e a kened roll_r esponse. Wit h t he wi n gl e t s ca at ed Ou t w a rd ( 6 w= +2 0 °), h o wev e r, t he a il e r ons ar e sho wnt o be a l m os t co m ple t e ly i ne ff e cti ve i n r o lli ng th e aircr a ft, w l t h a r o ll rev e r s al indicate d at ab o ut _ = 4 ° . Deflecti o n o f the c on tr o l s tick f o r ailer o n c o ntr o lin the s wathr u n w o ul d pr o duce rever s ed o r veryw e ak r oll re spo n se .
HANULING QUALITIES EVALUA T ION R E SUL T S Pi lo t-vehic l e perf o rm an ce_ab o ve the thre shold o f c o ntr oll abillty l ie s o n a c o ntinu o u s s c al era ng ingfr o mina d eq u ate thr oug h ad e q uate a nd d esirab l e.E a ch c ateg o ry c o n s titute s a l l n e s egm e nt o n th iss ca l e rathert h ana d iscrete p oi nt. F o r the s wathrun t as k,t h e des lrab l e perf o rmance en d o f the sp ectrum w o u ld be characteri z e d by o n l y s ma ll am pl it ud e track d eviati o n s an d s ma 11 , qu ickc o rrect io n s t o reac qu ire the reference l l n e. A d equ a te p er¢ o rm a nce w ould be ty p ifie d by a l arg e r r a ngeo f dev iation s and slowe _c o rr e ctlve r esponses un tl l r e a ch ing 1 1 ml t s ju dged t o be bou n d ary c ond iti ons o f t h is c at ego ry .Fo r t h i sev a lu atl on , th e boundari e s of th e s e cat e gori es iv e r e as s e s se d qualitativ e ly by th e simula tor p _ o t b y ob s e _ v t ng th e vi s u a l d ts pla y , R _ ul t s f o r t h e B a .s4c At r plane The bas t c atr pl a ne w as g t ven a Coope r -H ar pe.e r a ti ng o f 4 (see ft gu r e 4) an d exh i bi t e d seve r al mi no r d ef i c i enc i es, F i gu r e 11 s h o w san_ove r - : r head v i e w of a ty p t c a l g round t_ ack f o r ±h e b a s i c a ir p l ane , Th e figur e Il lu st ra t e s t he l eng t h o f _ t he ta x tw a y a nd it s cen t e r l t ne ( I 372- _ ), w h t ch _ represen t s abou t 25 secondsot' f l y tng t tme, An exp. a nded scale f o r t he t ax _ ay's w td t J _ ts used as an aid t,_v t sual t ztng t he a trplane._g ro und t r ack d e vi a t i ons f r om t he cente r l t ne re£ e r ence t r a ck, The.pilot-veh i cle pe r form a nce f or the b as f c a ir pl a ne c ou l d _b _ pl a ced near the bound ar y_ : bet w een t l _ e " adequ a te " a nd " desi r able" r anges on.the cen t tnuoussc a le . de s c r ibed a bove, W a rr a n t ed i m p r ovemen t s in t he a tr pl a n e w ould a llo w _: mo r e expedi t ious co rr ections_ r e t he r eference ltne and _ m a ller ampli t ude _ . dev t a tt .ons, Th e a bi li ty t o gene r a t e mor e s t de f Orce f o r a given std e _lfp : i . angle w ould have i mproved t he p e r foma n c e of t h i s con fi gu r a ti on so lon g _ .
!_ ' a s t h e b a nk con tr o l J _ d t d no t co r respond i ngl y t nc r eas e i n d if f i cu lt y, _ _ T he handllng qualities of the b a stc at _ pl a ne w e r e_c o ns i dered r epre- : _ sentattve o f th e behav 4 oro f agricultural a i rpl a nes and a r easonable J i basel i ne.
_ : Res u l ts for the _ ltnglet s Ca nted O u t 200 L : i ': ! The conflgura t lon w lth 6 w = ZO O wa s glven a Cooper-Harper r atlng
:I!
o f 7, t f the f ltght w asma i ntained within relatively small _ ;tdesllp i_i angles (+..10°), Fo r l a rge _ stdesltp a ngles, t htS config u r a tion would : som e ti m es r ol l off suddenl y , raptdly, a nd uncont ro llabl y , crashing !! 17 i mme d iatel y , Suchu nc on t ro ll a bl e r oll - offs Occu rr e d dur ing a bou t one - t e nt h of th e run s . F i g ur e IZ s ho w sa ty p icaltrackfor thi s conflg u ra - tlon. In addition to th e v e rypoorand s o me ti mes div e rg e nt trackin g p e rfoV_n a nc e , b a nNangl e c o n t r o l w as verypoor. A ltitud e control su ff e r ed as a con sequ enc e of high s i des lip e xc u r s ion s {cau s ing hi gh dr a g)and th e hlghd e gr ee of pil o t a tt e ntion r eq uir e d to cont r ol groun d track an d b a nk a ng l e .
T h e s e r e sult s we r e n o t un e x pe ct e d, consid e ring th e p re vio us ly - _ di s c u ss e d a e rodyna m ic lat e _al - d l rectlonal s tability and controlcharac - teri s tics of th e aircraft. T h e larg e incr e a se In dih e dral , e ff e c t_ d ue to th e w lngl e t s, in combination w lthth e d e cre ase In dir e ctional s tability , r esu lted in an e a s ily e x c ited Dutchrollmod e . T h e s _m u lat e d aircraft th use xp e ri en c e d e xc ess iv e r o lling m otionsfollo w ing th e r u dd e rinput s . In addition, th e ail e r o n s, w hichcould norma l l y b e us ed to Co u nt u ract any u n w ant e d rolling mo tion , we r e r e nd e r e d _Imo s tu se l ess by t he pr e se n ce of adv e rs e ya w du e to ail e ron d e fl e ction (Cn6a > O) and _: t he l a rge po _itt ve d ihed r a l e ff e ct.
The can t ed - ou t wtng l e t con fi gura ti on a l so s i gn i fican tly I ncre a sed )5 _ - C y 6 , Wh t c h t s des ir ab l e fo r u s e in g r ound tr ack corr e c ti ons. Th i S po t entia l bene fit w a s nega t ed b y t he excessive r O ll ing mom en t s genera t ed b y t he w l ngle t s. The p i lo t w a sable t o a c h ieve a dequa t epe rf o r mancewt t h 1 a c o ntr o l t echn i que _ ch requ i re d a n t n t ele ra ble wo r klo a d level; t he. = p i lo t usedno a t l e rOn i n p u t s bu t Onl y Ve r y h i gh f r equenc y r udde r / activity f o r con t r ol , i 1 8 Resul t s f or t he Wt ngle t s Can t e d i n 1 0 ° Th i s c o hft gu r a t ton w as g i ven a C oope r-H a rp e rra t i ng o f 3, F i gu r e 13 sho w sa ty p i c al g ro un d tr a ck f o r thi s con fi gu rati on a l ong wit h tr a cks for t he b a s i c a nd 6w = 2 0 0 c a ses. The r esu lt s i n di c at e a d e fi n it e i mp r ovemen ti n p i lo t / veh i c l e p e rf o ma nce r el a ti ve t o th e r e sul t s ob t a i ned wit h ou tward l y-c an t e d wt ng l e t s a nd f o r t he b a s i c a ir c r af t . T h e p tl o t 's w o r k l o a d in pe rf o r m i ng t he s wat h r un t ask w a s comp a r a b l e t o t h at o f t he b a s f c a ir c r a ft , a n d t he ove r a l l h a n dli n g qu a liti es w e r e cons id e r ed t o be b e tt e r th a n th ose o f t he b a s i c air c r a ft .
The im p r ove m e nti n h a nd li ng qua l i ti es o f _ t he ai r c raft wit h i n w a r d ly - c a n t e d wt ngle t s ove r t he b a s i c a ir c r a ft wa s d ue i n p art t o t he i nc rease i n -C yB . The h i g h side f o r ces gene rat e d b y t he wt ngle t s w hen t he air - c r a ft w a s s id es lip ped w e r e b e ne fi c ial f o r m a k i ng l a t e r a l co rr ec t ions.
An even g r e at e r i nc r e a se i n -CyB w a s ob t a i ne d w hen t he wt ng l e t s w e r e ,' ca n t e dout,but thi_ po t e ntial be ne fit wa s n e gat ed by t he fa c tt h atwh en t he aircraft w as s i desl i pped , excessive r oll i n g m o ti on sa nd b a nk-angl e -,, d i ve r genc e s occu rre d .I n s u mm a ry , o f th e t h r ee wi n g-tip c on fi gu rati on s s t ud ied, the aircraft wlthwinglet_ cante d inward10 0 was Ju d ge d t o have _ . th e b e _t h a ndl i n g qu a l iti es in th e s wathr_ a sk .
IN I _RPRE T A?ION OF R ES ULT S ; ,, The fid e l i ty o f t he s lm ul at lo n in r e pr ese nti ng an a c t ua la g r lcul t u r al : aircraft w as evaluate d by having a p il o twithagricultural aircraft ii. ex p erienc e fly the s imulat o r. T he s im u l a ti o n w a s v a lid a t ed t o the i -C_ _., extentth a tthe ba se line a ircraft ch a r a cteri s tic s wer e c on sidere d t o be : . ; _ ge n e r a lly r ep r esen ta ti ve o f ag rlc ul t u r ai a ir c r a ft.It shou l d b e ,(, ! .-,' , { ,
i : i
_L;_, _4_' r ec o gnized, ho w e _ e r , that t he present s t ud y wa s 11mttedtn t erms o f _ Si m u lat or h a rd w a r e a nd sof W a re , a n d these limitati ons s hould be kept tn : _ ,- m tnd whenapplytng t he r esults an d conclusions o f tht S stud y . S ome _ " f acto r s w h i ch I nt r oduced unce rt atn t , o s tn t he s im ula ti on ar e (11s t ed tn ._ o r de r o f their estf m ted I m po rt ance): ° ' a Simul at ion w a s ftxed b a se.- P i lo t loop closures mi gh t have been _ , ' di ff e r en t t f _ td_fnPc_ a nd r 011 a ccele r a t fon cues h a d been _ , . ava i la b le.
_, , ; _ 0 Visual cues were limited.- Lack of pe r iphe r al v t s t on could subst a n t i a ll y affect p i lo t pe rf or m ance.
0 Limtted validation of s i m ulation. - The s f mula t o r _a s validate d b y having a p i lot wit h a g ri cultu ra l a i r pl a ne experience f l y t t and i . t : i J udge tt t o be genera lly represen t a ti ve of t h i s t y pe o f a ir plane.
i . , i ; A m OPe cred i ble s im ula ti on w ould be mat ched t o actu a l f l i gh t data.
0 Lack of atmosphericdisturbances. - No t urbulence or wi nd inputs w ere used In t he stmul atf on. This w as con s idered t o be rela t ivel y : : u n i m portan t becauseo f the requ ir emen t f or low w tnd condi ti o ns f or man y a gricul t ur a l at r plane m_s s _ ons.
_ : In add i tion, the present stud y w as li m i t ed. In s cope, be t ng lt m tted t o onl y one area of _ h e opeP & tto ha l f l i gh t envelope, and onl y one task was used _ n t_e handllng q u a _it fes evalua ti on.
SI:]I _ ARY OF ' RES U L TS An explo r ato _j pt l o t ed s _ Ol'ater t_ ves ttga_ ion h a s been c onduc t ed t o ev at u a te the e ff ect of w_ ngle t s on' _ hj _ ha nd l' tn g qu a l lttes Of a _t! rep r esenta t i v e a gP l cul tu Pai afrP _ a n e dur4" _ J s _ h run ma neuvering . The - Ii
":ti
.. i follo w ing m a j o r r esults w e r e deriv ed fr om th is stud y : : 1. L at e ral - di r ection a l ha _l lng qu ali ties m a y be g r eatl y a f fected b y the ap p l icatio n o f w tng l e t s to thi s c l a ss o f a ir c ra f t .
2. W tnglet cant a ng l e c a n be used t o v a r y t he l eve l o f . d i hed ral effect a ndJ at e ral -d ir ec t tonal han dl tng qua l i t ies.
3. Pr oper ta . ll o rln g o f th e wl ng l e td es ig n may affor da po t en tial be ne fit I n t he are ao f hand l ing qua litie s d u e t o increa se d s idef o rce _ g ene r at i on _f o r m ak i nglate r a l co rre c ti ons i n the s w a th tun .
4. Stabll lty, con tr ol , and h a ndl l ng qual i t l es e v _ l, a tJ n j1s a r e need e d , i n ot h e r a r easo f t he f l ig htenve l ope , p a rtl cul a r l y a t h i ghang l eso f att a ck( e . g .,stallbe ha vi o r ) , b e f o re spe cific rec o mme nda ti o n s on. th e : use o f wl ngle t s f o r a gricultur a l air,raft c an be made.
R EFE R E NC ES I . J o r d a n, F r a nkL . ; McLem o r e , H. C l y d e ; an d Br a gg ,Mic h ae l B. : " S t a tu s o f Aer i a l A p D _l l c a ti o n s Rese arch in th e Lae _ le yV o rtex Fac i lity an d the L a ngley Full-Scal e Wi nd Tun n el. " NASA T M 78760 , _,_ 19 7 8 .
2 . J ohnson ,J osephL ., Jr . ; M cLemo r e , H. C lyd e; W h it e , Ri c h a r d; a nd J o rda n , F r ank L . . Jr.' " Full - Sc ale Wi nd*T u nn e l I nv e s ti g ati on o f an A yres $2 R_ 800T hr ush A gr i c ultura l Air plane ." Soc i e ty o f Aut o m ot i v e Engi n ee rS , N O. 790618 , 1979 .
3 . Fl e chn er, St uart G .& an d Ja cobs , Pete r F .: " Exp eri men tal R e su l t s ' , O f Wt ng l ets on F ir s t, Seco n d ,a nd Th ir d Gene ra t i on J et T ra n S po rt s. " N A SA T M- 72674 , 1 978 .
Z , . ,m 4. M echtl y , E. A.: " The Inte r nation a l system of Un t_ - Phy stc a l Cons t an t s a nd Conve r sionFac t o r s " ( SecondRevision). N A SA SP- 7012, l g 73.
5. Whit co m b,Rtch ar d T.: " A Design Approach a nd Selec t ed High SubsonicSpeed W ind-Tunne l Resul t s f o r Wi ng Tip M oun t ed Wi ngle t s. " N A SA TND-8260 , 1976.
6. Ho a k , E. E.;et a l.: "U S _ F St a bility a nd C on tr o l D A T COM, "A ir Fo r ce F lightDyn a mic s L a b,WPA F B,OH, F ebruary 197 2 .
7 . C op e_]_ land , Jame s L. (e d .): "Re s earch thr o ughSim u lati o n. '_ NASA N F -1 25 , 19 79 .
8. R o llin s , J o hnD. : "De s cri p ti on . a n d Pe rf O rmance o f th e La ng ley Vi s ual La nding Di s play S y s tem." NASATM-787 42 , 1 9 78 .
9. C oo per, G e o rge E .; and Harper, RObertP., Jr.: "TheU s e o f P il o t R a tin g in the Eval ua ti o n o f Aircraft Han d ling Qualitie s ."NASA TN D- 5 15 3 ,19 6 9.
2 2 I APPEND I X A DESCR I PT I ON OF EQU A T I ONS ANDDATA E M PLOYED I N S IM ULAT I ON Equationsof M o ti on The equa t ion s used t o desc r tbe t he mo t tons o f t he ai r p la ne w e r e n on- 1 1ne ar , s ix-deg r ee-of-f r eedom, rt g _J -bod y equ at tohs r efe r en c ed t o a bod y -fixed axis S y s temshownin ftguPe 1 a n d are given as follows: Forces: = r v - - .9s i n o + +!
• .- m C x, t m m = pw-ru + g cos 0 stn ¢ + 9 _ m Cy, t = qu - pv + g cos 0 cos _ + _ m S C Z, t Moments: , Iy - I Z IX Z _X p = -- I X q r + - _ X ( _ + pq) + Ct 't _- I Z ; y IX p r + -l-_y Z y Z ( r'- p2 ) _, I X ml II y I XZ . _ .
. iii I7 P q + -_7 ( _ " q r ) + C ri, t where th e total a e r o dyn am i cco e ff i c i e n t s C x, t , Cz, t , Cm, t , C y , t , C n , t , a nd Ct, t a pe d ef i ned tn t h e nex t sect i o n . Eu l ee a n g l es w e r e c om puted . b y using qua rt ernton s t o a llo w conti n u ity of a ttit ude mo t io n s.
• A uxlll a r y equatfons 4 nc i uded: 1 J
o . . .-I ( w)
v= V u 2+ v 2+ . 2
a n = qu.-pv + g cos c)cos @- g ay = -pw + ru - q g c os c)sin.@+ Aer o dynamic D a ta The aer o dynamic dataused in the s imulation wered e rive d fr o m lo w- spee d win d -tunnel te s tsof the ful l -scale aircraft and o f a I / lO-sca l e model o f the configurati o n at the NASALangley Re s ear c h Cent e r. The staticaer o dynamics and d Ynami L d atawere inputin tabu l ar f o rm as a function of angle o f attack o verthe range 0 < _ < 20 0 . T o tal c o efficient equati o ns w ereusedto s um the vari o u s aerodynamic c o ntri- buti o ns t o a givenforce o r momentcoefficient a s f o l l ows.
F or the X- and Z-axisf o r c ecoefficient s : CX,t = - CD,t cos a t sin _ C Z, t = - C D, t s in _ - C L , t cos w l _ e re CL, t = CL (_, 6w) + CL (_) 6e + A CL,g e (eL,h) 6e CD,t = C D (ct, 6w) + A C D,6e (c_, 6e ) + ^ CD,ge (CD,h) Fo r t h e p ttthtng-monlen t co eff ici e n t : C m , t ,, C m ;_ ) + C m6 e ( c_ ) 6 e + C m q( r pm) _ . + A C m ,g e (C m h) Fo r t he Y-axls f o r ce coe ff icien t : " Cy_ Cy, t Cy _(_ ) _r + ( =, _w ) B Fo r t he y awing- m omen t coe ff icien t : + (_) Cn , t = Cn ( _ ) 6r + Cn ( _ , 6w ) 6a + ( _ ) rb 6 r 6a Cnr Cnp +C n 8(_, _w ) B Fo r th e r ol ll ng- m o me n t coe ffici en t : C_, t = Ct (_, 6w) 6a+ct (_)6r+c t (a)_-_+Ct (_,6w) 6a _r. P r rb _F + C_ (_, _w )B B T h e a e r od y n ami c coe ffi c i en t s co ntained in t he p r ece di ng co effi c ient eq u a ti ons a r e p r esen t ed f o r trtm cond it i on s a t th e ope rat ing speed f o r t h e s w a t h run. The a e r od y na mi cmo m en t coe ffi c i e nt s a r e r e f e r enced t o a / ce n te r- o f- g r avit y loc at ton o f 0.30 _ . . / E n gine S im ul a t i o n Pr e sent ed tn t able IV ar e t hru st val ues a s a fu nc t ton o f v e l oc ity a nd . e n g in e r pm, with e n gi n e rp m a s a f uncti o n o f thr o ttl e pos it io n .
2 5 TABLE I . - MASS ANDDIMEN S IONAL CHA _ CTERIST I CS USED I N S IMULATION W etgh t , N (lb) ......................................... 346 9 6 (7800) Home nt so f tne rt ta, kg -m 2 ( s iu g - ft 2 ) : Bas t c a ircr a ft I x ................................................ 6957 ( 5131) Iy ................... _............................ . 7572 (5 _ 5) I Z ................................................ 13996 (10323)
i xz ............................................... 6 6 ( 4 9)
Air c r a f t wit h w lngle t s I x ................................................ 6995 ( 5 1 59) Iy ................................................ 1 572 ( 5585) • I z ----- ............................. -- -- - - - --- - - - - 14034 (10351) ------ - ------------ - ------ ---- - -------- 66 IX Z ........ (4 9 ) Win g dim ensionS: S p a n, m (ft) ....................................... 13.53 (44.4) , A r ea , m 2 ( ft 2) ............................... _..... 30.34 (326. _ ) M ea n ae r od yn amiccho _, m (ft) ..................... 2.29 (7 . 5) R e f e r ence cente r - o f - g r avi t y loca ti on ........................... 0.30 _ Su rf ace de f lection 1 1mt t t, de g : E le va tor ................................................ +17, -27 Atle r ons ................................................... +38 Rudde r s ..................................................... +24 T A BLE II. - A E R ODYN AMIC DAT A USED I N SIMU LAT I O N A t swa th r un co ndltl ons ( I - g tri m, V=120 mp h , h=3m o r 10 ft) B a s i c 20 0 6w - 10° Air c raft 6w- = = a 4 . 31 3 . 42 3 . 42 CL . 63 7 . 636 . 636 CL .nn_q q . 0058Z .0 05 8 7 6e :_ ACL, g e .14 8 . 14 8 .14 B CD .094 0 .095 5 .0955 - .00 0 24 7 - .000623 - .0 0 0623 A CD , 6 e A C D,g e -. 0084 4 -. 00893 -. 0 0 893 C m . 0341 . 0397 .0397 C m - . 0152 - .0150 - . 0150 6 e C mq . 23 0 .230 . 23 0 ACm, g e -.002 7 4 -.00 3 1 8 -. 00318 C y .001 7 2-- .OO C 7_ l_ . 0 0 171 • C y _ r - , 0 061 -.01 28 -.00 94 Cn . - . 0 0 0 569 - .00 05 70 - .00 05 7 0 6r C n .00 0 09 8 . 00 01 57 .000 15 7 6a C nr -.001 3 9 -.001 2 8 -.001 39 Cnp -.0007 36 -.0 006 44 -.000 63 B Cn .0004 3 _ .00 03 90 .0004 5 9 B C I -.00169 -. 0 0190 -.001 9 0 6a C_ .000171 .000165 .0001 65 6r Cl -.00 7 92 -.0080 3 -.00792 P C_ . 0 03 4 5 .00 6 08 . 004 34 r C _ -. 00157 -.0 0 4 49 -. 00258 B Q t T A BLE I II .- LAT E RAL-DIRECTIONAL S TAB I L I TY C HAR A CTERISTICS IN S W ATH RUN I-9 t rl m, V - 120 mph CONFIGU RA TIONPDR CDR (¢ / B )DR ZR B a s i c 4.34 .246_ 1.34 -173 68.0 _w = 3.54 " .201 4.21 _ .171 10.8 6 _ = - 100 3.96 .223 2 . 27 .1 73 19.9 TA B L E IV._ T HRUS T VALU ES . _ S ED I N S I MU L ATI O N (a) SI U NI TS Th r ust values (N) a t a veloc t ty ( m / sec) o f - i i i 6T 1"131 1 1 31 36 40 ,45 49 I 54 58 63 6 7 •1 1000 1047 73 4 44 0 1 0 6 -249 -60 4 -959 - 13 1 4 - 1669 .9 2400 8356 8211 8065 7917 7751 7553 7317 7006 6497 ( b) U . S, C USTO M AR Y U NI TS Th r ust values (l b) at a ve l oc i ty (m t / h r ) o f - i
_T _pm 7 o _ o _ o l oo 21 o 12 o 13Q24 o 1s o
.1 100 0 235 165 99 24 - 5 6- 136- 2 16 - 295 - 375 . 9 2400 187 9 1846 1 8 13 178 0 1743 1698 1 6 45 1 5 1 5 1 4 61 g 2 :';: - _. ....
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Fig u re 10 . -Variation oflateral control div e rgenc e paramet e r
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• configurations. I
J _ ' N o. I 2. O N_,_ 6 , _ No . _ . _ . ¢ i p,m' s C,, S o, No.
H -81 B 17 [ I 4 .Tits , _ _b_it_ , _. S _ o on D _ .
IEXPLORATO R Y I _ ILOTED SI M ULATO R STUD Y OFTHEEFFECTS A pril 198 0 IOF W INGLETS ONHANDLING Q UALITIES OFA REPRESENTATIVE s. e _ m ing Or _ n i z, ti_ co _ A G RICULTURA L AIRPLANE 7. Author(s ) 8 . Performing Orgllni z lltio n Rel _ ortNo.
Ma r |l yn E. Ogburn a nd Pht l tp W . Brown I0. Wor k Unit No.
9. Performing O re a mi z _ tiofl _ e n d Addr us b 05-41 - 83 - 01 NASA Lang l e y Resea rc hCen te r li . co, _ , ¢ t o , G, . , t N o.
Hampton,VA 2 3665 , 13. Typ e of Report and $k e r io d C o ve t e d 12. Sponsoring AgencyName a n d Address. Tec hn t c a 1 Hemo r andum N a ti ona l . Ae r onau ti cs a nd SpaceAdm i n i s tr a ti on 1 4. s p o n_ , _A_r_ " _ : VJ aSh in gton. D.C. 20546 i m :1 6 _S u p p l e m en ta r y Nora .
16. A _ u e _ A n exp lor a tory pil o ted si m ul a t o r s t ud yha_ b een c o n duc t e d I n o r de rt o ev a l ua t e t he e ff e ct s On ha n dling q ualltl e s of a d dlngwinglet s to a repr e sentatlv e agric u ltural aircraft confi g uration d urin gs wathrun m an e uv e ring. T h e a erodyna m ic d a tau s e din the s i m ulation w e reba s e don low -s p ee d win d- tunn e l t e s t s of a full-sc a l e airplan e - and a ) ' su b Scalemode l . T h e s tmulatfo n wa s condu ct edon t he Langle y G ene r a l Purpose Sim u lat o r .__ The Coope r -Ha r pe r hand lt n9 qu aliti es rati ng scal e , supp l e m en t a ry p tl o t c ommen t s a nd p il o t -veh icl e pe r formanceda t a we r e used to des cri be t he ha n d lf ng aual ttt es o f )he airplane w ith t he di ffe r ent wlng-tlp configuration s .
Th e resu lt s of the Investlg@tlon s ho w edthat , for the ta s k e v a luated, th e later_l - dlrectlonal handling qualities of th e airplan e weregreatly aff e c t e d by the a_! ii ication of wlngl e t s and wlngl e t c antangle. The airplan e w ithwingl e ss cant e dOut 2 0 n exhibited severely degrad e d lat e r a l- d irectional handling q ua)Itles In c ompar i s on to the basic a lrplane.Wh e nthe wlnglets w erecantedinwardI0O , t h e flyingqu a lltl es of th e con - figuration were m rkedly improved overtho s e of the wlngl e t - canted o ut configuration or the ba s i c confl g urat!on without wlngi e t s , indicating thatpropertailoring of the wlnglet d esign m ay afforda p o tential b e nefitin th e ar e aof handling qualitie s .
1 1 . K _ V W or d s ( Sug p lt e d b y A uth or l s l) 18 Dist r ibut i on Stetement wtn g l e t s, dihedra l effec t , h an d l tn g u N C LASS I F I ED - UNL I HITEO : . I: quali t ies, swa th r un | , 19. ,_ k _ u r *tyOe _@. (o @ thisrep or t ) 20 . _ c ur ,tv Cl a m # .(o f this pe gs) 21 . No . o f Pi lgH 22 . P vl ce" ' . U N C LASSIFIED UN C LA SS IFIED 42 A 0 3 _ . _0_ Fo rs alebyt h eNat _ 0n a l Techn,c a l I n f _ m a hon S e rw ce. Sp r m _ held . V. _ m _ a 22161