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NASA Technical Memorandum '81 232 . > USAAVRADCOM TR- 81- A- 23 !NASA-Td-81222) EXPBBIbBU1AL AUD AIALYTICAL STUDIES OF A MODEL BBLICOPTBB iioeon 11 HOVER (IAS-) 61 p HC AO4/flP A01 CSCL OlA Unclas 63/32 08413 Experimental and Analytical Studies of a Model Helicopter Rotor in Hover F. X. Caradonna and C. Tung September 1981 Nat~onal Aeronautics and Space Admlnlstrat~on Un~ted States Army Aviation Research and Development Command

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Page 1: Caradonna Tung

NASA Technical Memorandum '81 232

. >

USAAVRADCOM TR- 81- A- 23

! N A S A - T d - 8 1 2 2 2 ) EXPBBIbBU1AL A U D A I A L Y T I C A L STUDIES OF A MODEL BBLICOPTBB iioeon 11 HOVER ( I A S - ) 6 1 p HC A O 4 / f l P A 0 1 CSCL O l A

Unclas 63/32 08413

Experimental and Analytical Studies of a Model Helicopter Rotor in Hover F. X. Caradonna and C. Tung

September 1981

Nat~onal Aeronautics and Space Admlnlstrat~on

Un~ted States Army Aviation Research and Development Command

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- 4 . -- NASA Technical Memorandum 81232 USAAVRAOCOM TR-81-A- 23

Experimental and Analytical Studies of a Model Helicopter Rotor in Hover F. X. Caradonna C. Tung, Aeromechanics Laboratory

AVRADCOM Research and Technology Laboratories A~nes Research Center, Moffett Field, California

1Jn1Ied States Army Aviallon Research and Development Command St LOUIS. Mlssour~ 631 66

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EXPERIMENTAL AND ANALYTICAL STUDIBS OF A XODBL HELICOPTER ROTOR IN HOVER

F. X. Caradonna and C. Tung

Aeromechanics Laboratory U.S. Amy Research and Technology Laborator ies (AVRADCOH)

The present study is a benchmark test t o a i d t h e development of var ious r o t o r performance codes. The study involves simultaneous blade pressure measurements and t i p vortex surveys. Measurements were made f o r a wide range of t i p Mach numbers including the t ransonic flow regime. The measured t i p vor tex s t r eng th and geometry permit ef feccive blade loading pred ic t ions when used as input t o a prescr ibed wake l i f t i n g surface code I t is a l s o shown tha t wi th proper inflow and boundary l aye r modeling, the s u p e r c r i t i c a l flow regime may be accura te ly predicted.

SYMBOLS

A r a t i o of vortex c i r cu l a t i on t o maximum blade-bound c i r c u l a t i o n

aspect r a t i o

Ck sec t iona l l i f t coe f f i c i en t

d r a d i a l d i s tance from a vortex t o a flow-f i e l d point

R radius of the ro tor blade

r r ad i a l d i s tance from the ro tor cen te r of ro t a t i on

Vi vortex-induced ve loc i ty

VR res idua l v e l i ~ c i t y i n the wake

y r/R, nondimensional r a d i a l coordinate

z a x i a l d i s tance from ro to r

ro t a t i ona l speed

Y azimuthal angle measured from the point of blade overhead passage

YV vortex age, the azimuth angle, Y, when vortex s t r i k e s t h e probe

- *Presented a t the Sixth European Rotorcraf t and Powered L i f t A i r c r a f t Forum,

September 16-19, 1980, B r i s t o l , England.

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1. INTRODUCTION

The p a s t two decades have seen a con t inu ing development of methods t o p r e d i c t r o t o r hover performance wi th i n c r e a s i n g accuracy. These methods i n c l u d e l i f t i n g l i n e ( r e f s . 1-3), l i f t i n g s u r f a c e ( r e f s . 4-6). and f i n i t e d i f f e r e n c e ( re f . 7) methods. P r a c t i c a l l y speaking, none of t h e s e methods is sel f -conta ined; they a l l r e q u i r e t h e s p e c i f i c a t i o n o f e m p i r i c a l l y obta ined wake d a t a ( s t r e n g t h and geometry) i n o r d e r t o have a c o r r e c t downwash d i s t r i b u t i o n . I n e v i t a b l y , t h e development o f t h e s e codes becomes a tun ing process i n which i t is determined j u s t how d e t a i l e d and a c c u r a t e a . . wake d e s c r i p t i o n must be. Th is s t a g e of code development p laces g r e a t r e l i a n c e on t h e a v a i l a b l e body of experimental r o t o r da ta .

. , The a v a i l a b l e r o t o r d a t a inc lude a s i z e a b l e number o f tests where d e t a i l e d b l a d e

loading is obta ined us ing s u r f ace p r e s s u r e t r ansducers ( r e f s . 8-1 1) , and mre r e c e n t l y by laser doppler velocimetry ( r e f s . 12-14). There is a l s o a number of tests i n which t h e r o t o r wake geometry is def ined by flow v i s u a l i z a t i o n techniques ( r e f s . 3 and 5) f o r a wide v a r i e t y of b lade conf igura t ions . Of t h e v a r i o u s wake s t u d i e s , o n l y Boatwright ( r e f . 15) and Cook ( r e f . 16) made d e t a i l e d i n v e s t i g a t i o n s of t h e wake flow s t r u c t u r e s . Cook's work is e s p e c i a l l y s i g n i f i c a n t i n t h a t he was a b l e t o measure t h e s t r e n g t h of the t i p v o r t e x by a c u r v e - f i t t i n g technique us ing hot-wire d a t a . However, t h e r e seem t o be no useab le d a t a i n t h e l i t e r a t u r e i n which simultaneous b lade load d i s t r i b u t i o n and wake measurements a r e made.

I t is the ~ n t e n t i o n of t h e p resen t s tudy t o h e l p f i l l t h i s gap i n tile l i t e r a t u r e . This paper w i l l d e s c r i b e t h e experimental set-up i n which s teady blade p ressures were obtained using hub-mounted t ransducers and t i p v o r t i c e s were measured us ing Cook's technique. The d a t a obta ined a r e f o r u n s t a l l e d flow ranging from t h e low subsonic t o t r anson ic cond i t ions . I t is shown here in t h a t t h e measured wake geometry d i f f e r s s i g n i f i c a n t l y from prcviously published low-aspect-ratio d a t a ( r e f . 5). Th is d i f f e r - ence i s r e f l e c t e d i n an i n a b i l i t y t o c o r r e c t l y p r e d i c t t h e measured blade load ing (us ing Summa's prescr ibed waki? l i f t i n g s u r f a c e code ( r e f . 6 ) ) when t h i s c l a s s i c a l wake geometry is used.

2. THE EXPERIMENT

The d a t a presented i n t h i s paper were gathered i n t h e Army Aeromechanics Labora- t o r y ' s hover t e s t f a c i l i t y , a l a r g e chamber wi th s p e c i a l duc t ing designed t o e l i m i n a t e room r e c i r c a l a t i o n . The r o t o r , s i t u a t e d i n t h e c e n t e r of t h e chamber, w a s mounted on a t a l l column con ta in ing t h e d r i v e s h a f t ( f i g . 1 ) . The r o t o r employed two c a n t i l e v e r - mounted, nlanually a d j u s t a b l e blades wi th ha l f degree precone. These b lades used an NXCA 0012 p r o f i l e and were untwisted and untapered. An aspec t r a t i o of 6 was chosen i n o rder t o maximize Reynolds Number and a v a i l a b l e ins t rumenta t ion space. The b lades were grooved t o accommodate 60 p ressure tubes each. These tubes connect t o a s p e c i a l c l u s t e r of t h r e e 4888 Scanivalves (us ing Statham PA 856-15 t ransducers ) d r i v e n by one SS5-48 solenoid d r i v e mounted i n t h e r o t o r hub. This arrangement permits an ample number of p o r t s f o r f i v e measurement l o c a t i o n s - t h r e e r a d i a l l o c a t i o n s on each b lade , with one l o c a t i o n being i d e n t i c a l on both blades f o r comparison purposes. The Scanivalve s t e p p e r motor was ac tua ted by a d i g i t a l d a t a system which acquired t h e d a t a , computed t h e c e n t r i f u g a l p ressure d rops , and displayed t h e f i n a l p r e s s u r e d i s t r i b i i t i o n . A f t e r manually a d j u s t i n g t h e two b lades , t h e p r e s s u r e d a t a was a l s o used t o check t h e e q u a l i t y of loadings . The p ressure d a t a a t t h e 0.8 R r a d i a l s t a t i o n a r e compared f o r t h e two b lades i n f i g u r e 2. No s i g n i f i c a n t d i f f e r e n c e s i n t h e

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loadings were seen f o r any operat ing conditions. ( ~ d d i t i o m l ind ica t ion of this loading equal i ty is tha t no cons is ten t d i f fe rence i n the hro shed vo r t i ce s was found.) The r e su l t i ng pressure d i s t r i b u t i o n s f o r c o l l e c t i v e p i t c h rettiqp of So, 8'. and 12' a r e shown i n f i gu res 3, 4, and 5. These and o the r pressure d i s t r i b u t i o n s a r e tabulated i n appendix A. It is seen i n f i gu res 3, 4, and 5 t h a t t h e inboard pressure d i s t r i b u t i o n s a r e only s l i g h t l y a f fec ted by ro to r speed. However, t he outboard sec t ions show conside:.lble pressure a l . t e ra t ion and shock development as the t i p Mach number approaches near sonic values. Overal l , however, t he spanwise load d i s t r i b u t i o n (obtained by pressure in tegra t ion) is ranarkably l i t t l e a f f ec t ed by t i p Mach number ( f ig . 6 ) . I n addi t ion , the t i p preesures were compared with those of reference 11 and a r e seen i n f i gu re 7 t o be nearly i den t i ca l .

Wake da ta were acquired with a traverse-mounted DISA SSP01 hot-wire probe mounted beneath the ro tor . The probe was or iented with the wire being tangent t o t h e ro to r t i p path. This permits measurement of the magnitude of t he vortex induced ve loc i ty when the remainder of the ro to r downwash is properly accounted for . I t a l s o excluded the e f f e c t of a x i a l ve loc i ty on the induced ve loc i ty measurement. Dzta from the wire a r e acquired a t var ious points along the t i p vortex t r a j e c t o r i e s and can give bcth the t i p vortex geometry and s trength. One problem with t h i s approach is t h a t the vr --tex t r a j ec to ry is not steady and the probe locat ion (which is chosen by an on-the- spot decis ion a s to where the number of vortex core "hi ts" is maximized) contains some a s yet undetermined e r ro r . The r e su l t i ng da ta stream has considerable v a r i a b i l i t y . However, i n order t o be c e r t a i n of the vortex loca t ion , the only acceptable da t a a r e chose where the vortex core ac tua l ly h i t s the prcbe. In the d i g i t i z a t i o n process (done o f f - l i ne a t a reduced tape speed), t he above-mentioned da t a system was coded t o look for and accept only those da ta which showed the c h a r a c t e r i s t i c s igna l d i p (wherein the m i r ~ i m u m ve loc i ty is very c lose t o the vortex t r ans l a t ion speed) which ind ica tes a probe-vortex s t r i k e . This titrns out t o be a very small percentage of the t o t a l mount of da t a ac tua l ly recorded. A t yp i ca l hot-wire t r a c e displaying the above-mentioned v a r i a b i l i t y is shown i n f igure 8.

3. HOT WIRE DATA ANALYSIS

The idea of the current da t a ana lys is is tha t a t i p vortex should look l i k e an i n f i n i t e l i ne vortex t o a s u f f i c i e n t l y c lose probe. Unfortunatly, the probe mea- surcs not only the ve loc i ty induced by the vortex a t hand, V i , but a l so tha t induced by thc blade and the remainder of the wake system a s well , VR. The problem i n analyz- i n g the probe da ta is , then, how t o separate t h i s res idua l ve loc i ty , VR, from the immediate vortcx-induced ve loc i ty , Vi. Cook ( r e f . 16) handled t h i s problem by assum- i n g tha t the res idua l ve loc i ty was constant and given by the t r ans l a t ion ve loc i ty of t h e t i p vortex. Ht! then was ab le t o find the vor tex s t r eng th by a f i t t i n g process. This s t rength was found t o be f a r l e s s than the computed maximum blade bound c i rcu la- t ion of the s ing le , fu l l - sca le blade used i n t h a t t e s t . It was a l s o found tha t t he vor t ices measured were d i s t i n c t l y nonclassical i n t h a t they contained a la rge rota- t i ona l region outs ide of the viscnus core. In what follows, we s h a l l use a process very s imi la r to Cook's i n analyzing wake data .

F i r s t consideration is given t o the vortex t r a j e c t o r i e s . Figure 9 shows the .luial and r ad ia l components of the vortex t r a j e c t o r i e s f o r a p i t c h s e t t i n g of 8'. 'Chi5 f igure gives da t a fo r a wide range of ro to r speeds, and i t is apparent t h a t the t r a j ec to ry is e s s e n t i a l l y independent of t i p speed - even i n t o the t ransonic r e g h e . Flgr~re 9 together with f igure 6 suggests t ha t the nonlinear t ransonic flow on the b l n d c has l i t t l e e f f e c t on the f a r - f i e ld induced flow as long a s the loca l l i f t is

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not grea t ly a l te red . Also p lo t ted on t h i s f i gu re is t h e vortex t r a j ec to ry given by Kocurek's wake-fit t ing formula f o r r o t o r s i n f r e e a i r . Although the a x i a l component of the t r a j ec to ry compares wel l with Kocurek's formula, t he re appears t o be a g rea t e r discrepancy i n the contract ion than can be explained by measurement e r ror . The vor tax t r a j e c t o r i e s f o r p i t c h s e t t i n g s ranging from 5 O t o 12' a r e given i n figure 10,

The present aim i n analyzing the ro to r wake is only t o f ind t h e vor tex s t r eng th and not a complete descr ip t ion of the s t ruc tu re . This s t r eng th w i l l be found by f i t t i n g the wake da t a t o the v e l o c i t i e s obtained from an appropriate combination of inv isc id , two-dimensional vor t ices . The ve loc i ty from one such vor tex is given by

where the s t r eng th of the vortex is described by A, the r a t i o of the vor tex c i rcu la- t i o n t o the maximum bound c i r cu l a t ion of the blade. (This could be determined by the pressure da t a because the c i r c u l a t i o n peak is not very sharp and is qu i t e c lo se t o the t ap locat ion.) To accomplish t h i s f i t t i n g , it is f i r s t necessary t o convert the s p a t i a l l y dependent equation (1) i n t o a time-dependent expression, a s t he vor ex da t a a r e time-based, Assuming tha t A is constant (which seems t o be t r u e within reason- ab le e r r o r bounds), t he conversion t o a time-dependent function is accomplished by expressing d a s a function of time using the vortex t r a j ec to ry da t a of f i gu re 9. The next s t e p is the de te rn ina t ion of the res idua l ve loc i ty , VR, which must be vec- t o r i a l l y added t o V i before a comparison can be made with the probe data . We have done t h i s i n two d i f f e ren t ways:

1 ) The first way t o determine VR involves very young vo r t i ce s (about 50" o ld ) . For these i t was assumed t h a t VR was given by the vortex t r a j e c t o r i e s ( f ig . 9). The f i t t i n g process always commenced when the vortex core h i t the probe and ended when the following blade passed over; t h i s assured the simplest possible flow f i e l d , a s t he re would be vo r t i ce s on only one s i d e o f the probe and minimal i ~ f l u e n c e of vortex shee t s and blade bound v o r t i c i t y . Figure 11 shows some typ ica l con ~ r i s o n s of probe da ta with the f i t t i n g expression. This f igure shows the vortex velocity-time t r aces f o r p i t ch s e t t i n g s of 8' and 1 2 " . I t is seen here t h a t the f i t t i n g curve provides a good match t o the da t a outs ide of the immediate core region. Furthermore, the vortex s t rength is very close t o the maximum blade bound c i r cu l a t ion .

2) A second means t o determine VR was required i n analyzing older vo r t i ce s (about 210" old) . The flow is more complex i n t h i s case, a s the probe always l i e s between two vor t ices i n the f i t t i n g region, and the expression f o r the vortex-induced veloci ty is correspondingly complicated. In f a c t , V i f o r t h i s case was determined using three vo r t i ce s - one outboard of the probe and two inboard. Again, the data were f i t f o r the time period between a probe-vortex s t r i k e and the subsequent blade passage. It was found tha t with VR determined by the vortex t r a j ec to ry da t a , i t was trot possible t o obtain a good f i t of the c l a s s i c a l vortex expression t o t t ~ e wake data . Instead, w e found t h a t a b e t t e r value fo r VR was found by w e of the minimum meb- sured ve loc i ty between two vor t ices . A t t h i s point , the vortex-induced ve loc i ty is :.mall, but not zero (due t o the d i f f e r i n g instantaneous t r a n s l a t i o n v e l o c i t i e s of the three vo r t i ce s ) . The minimal induced ve loc i ty is calculated (assuming some value of A) and subtracted flom the minimum measured in te rvor tex ve loc i ty t o obta in 1'~. This task was rendcred q u i t e simple by the f a c t t ha t the r a d i a l component of these veloc- i t i e s tu rns out t o be very small ( t h i s was checked by ca lcu la t ions and measurements with a second probe). Since the two methods above do not give the same value f o r the res idua l ve loc i ty , i t is c l e a r t h a t VR is not a constant i n t h i s case. We assume,

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however, t h a t i t changes s u f f i c i e n t l y slowly t o render t he f i t t i n g proceee meaning- f u l . I n f a c t , t he r e s u l t s thus obtained a r e coneis ten t wi th the young vor tex data . Figure 12 shows some t y p i c a l comparisons of t he o lder vor tex d a t a with t h e f i t t i n g expressions. This f i g u r e shows t h e f i t t i n g s f o r p i t c h s e t t i n g s of So, 8'. and 12'. It is seen t h a t t he 8' and 12' cases show vor tex s t r eng ths which match t h e maximum blade-bound v o r t i c i t y very w e l l . A t 5' p i t ch , however, t h e s t r e n g t h is seen t o be

w considerably smaller.

It seems from the above da ta , which a r e taken at a low r o t o r speed, t h a t t h e t i p

,. vortex develops i ts f u l l s t r eng th very e a r l y i n l i f e (mainly before 50'). Although

.\ there is a f a i r amount of v a r i a b i l i t y between vortices, it is r a t h e r s t r i k l n g t h a t very many vo r t i ce s c lo se ly approach a c l a s s i c a l Rankine vor tex i n appearance. Fur- thermore, the vo r t i ce s (except f o r t he So case) seem t o contain a l l of t h e blade c i r cu l a t ion . This vortex s t r eng th and s t r u c t u r e d i f f e r s markedly from the r e s u l t obtained by Cook and probably r e f l e c t s t he considerable d i f fe rences i n blade geom- e t r i e s . A s ro tor t i p speed increases ( f ig . 13). however, t he re appears t o be an increasing departure from the Rankine vor tex appearance. Nevertheless, t he nondimen- s i o n a l vortex s t r eng th seems unaffected by t i p speed.

4. COMPARISON OF THEORY AND EXPERIMENT

In order t o i n t e g r a t e t he present wake and loading da t a i n t o a bel ievable whole, i t is necessary t o be ab le t o reproduce the blade loading computationally. We have f chosen t o do t h i s using A.M. I. ' s l i f t i n g sur facz code ( r e f . 6) . This is a very f l e x i b l e , compressible, l i f t i n g sur face code which can handle e i t h e r prescribed o r f r e e wakes.

I n i t i a l e f f o r t s t o compute the blade loading were done us ing t h e Kocurek wake geometry ( r e f . 5) . The r e s u l t i n g computed t h r u s t coe f f i c i en t was too high by about 20%. The next s t e p was t o compute the loading using the measured vor tex loca t ions and s trength. Figure 14 shows a comparison of the measured and computed loading using the measured vortex parameters f o r a c o l l e c t i v e p i t ch of 8' ( the t r a j e c t o r y is given by f i g . 9 and we choose A = 1.0). The comparison is now considerably improved and the thrus t coe f f i c i en t is overpredicted by l e s s than 5%. I n view of t h e previously men- tioned unce r t a in t i e s i n the vortex t r a j e c t o r y measurements, these computations were a l so performed with the e n t i r e vortex t r a j e c t o r y perturbed such t h a t a t Y = 180°, the a x i a l and r a d i a l per turba t ions were t0.025 R. The r e s u l t s derived from a l l possible conbinations of these a x i a l and r a d i a l changes f i l l t he shaded area i n f i gu re 14. That t he above measured and computed r e s u l t s a r e roughly centered on t h i s shaded region ind ica t e s t h a t f o r t h i s case the measured t r a j e c t o r i e s a r e f a i r l y accu- r a t e . However, the bes t comparison with the measured loading occurs when the vortex r a d i a l loca t ion ( a t Y = 180') is increased ( tha t is, the cont rac t ion is decreased) by 0.025 R. The i d e n t i c a l s i t u a t i o n was found t o occur i n computations of t he 12" p i t ch cases; t h a t is, the bes t comparison occurred when the r a d i a l vortex loca t ion was increased by 0.025 R over the measured value ( f ig . 15). For t h e 5' co l lec t ive- p i t ch case, the s i t u a t i o n was a l i t t l e d i f f e r e n t i n t h a t a reasonable comparison of computation and loading d a t a could not be made u n t i l the vortex s t r eng th was reduced t3 A = 0.75. In t h i s case, the v o r t i c i t y which would otherwise have been i n the t i p vortex was now included i n the vortex shee t model. (For a complete desc r ip t ioc )f the assumed vortex sheet model s ee r e f . 6.) This r e s u l t is cons is ten t with the mea- sured vortex s t r eng th and gives the comparison shown i n f i gu re 16.

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The previous comparisons have been made a t low t i p dach numberr. The l i f t i n g sur face code used should be appl icable t o pred ic t t h e epaasiee m d chordwira loadin8 up t o t he onset of s u p e r c r i t i c a l flair. Beyond t h i r point , l i n e a r aerodpnrr icr are not appl icable on t h e blade and a more complete flow desc r ip t ion is requi ted. AD a preliminary evaluat ion of t h e high-rpeed flow da ta , two-dimensional computations were made of the flow a t t he 80% r a d i a l s t a t i o n . This was done w i n g Holet ' s f u l l - p o t e n t i a l code ( r e f . 17). I n order t o perform t h i s computation, an angle of a t t a c l r i a required. Since t h e region of supersonic flow is l o c a l i t e d ( i .e . , l imi ted t o t h e i aned ia t e v i c i n i t y of t he upper blade surface) , i t should be poss ib le t o f i nd the awle of a t t a c k using the l i n e a r l i f t i n g sur face code. Of course, the l i f t i n g su r f ace code require. the measured vortex loca t ion and s t r eng th as awntioned previously. With t h e angle of a t t ack obtained thereby, t h e Holst code produced t h e r e e u l t s shown i n f i gu re 17. Th i s f i gu re shows two ccmputed r e s u l t s - an inviac id r e s u l t and one wi th a viscous ramp- boundary layer model ( r e f . 18). It is seen t h a t a shock-boundary l aye r i n t e r a c t i o n model is very necessary and i n t h i s case very e f f ec t ive .

5 . CONCLUDING REMARKS

The present study was intended a s a benchmark t o a id i n t he development of hasrrr I_

performance codes. The goal was eo obta in s i m l t a n e o u s measurements of blade loail d i s t r i b u t i o n and t i p vortex geometry and s t r eng th using f a i r l y standard techniqries. In s p i t e of some unce r t a in t i e s (due mainly t o wake unsteadiness), l i f t i n g sur face computations show tha t the present measured loads and wake measurements are generally consiscent with each o ther .

The main conclusions from t h j s study are :

1. The Cook vortex measurement technique seems t o be q u i t e e f f v c t l v e Ic7r t w - bladed rotors .

2 . A t low ro tor speeds, an untwisted, untapered, double-blade4 rot:~l;- prcriuces t i p vo r t i ce s which can c lose ly resemble a classicaf . Rankine vortex. % s c r t ~ ~ i i o r t he lowest p i tch s e t t i n g s , t h i s vortex s t r eng th c lose ly approaches t h e ; I I P T ~ ~ ~ U D blade bound c i r cu l a t ion . A t higher ti; speeds, the inner vortex s t r u c t u r e appear? ?r:creasingly nonclassical ; however, the s t r eng th is unal tered.

3. I t is not possible t o predict the blade-spanwise-load d?..itr ' i6:.t:.f~n without accurate vortex loca t ion and s t r eng th data . The present meaaurA v o l i , ( u l o c ~ t i o n da ta were s ign i f i can t ly d i f f e r e n t ( for present ly unknown re.ss<iru+ :rorL tbc~ r ' l i ;ssical da ta i n the l i t e r a t u r e . However, these measurements were sr..o?a:;ei?s;S',e io obtaining a reasonable comparison of theor- and experiment.

4 . For the present r o t o r and speed range t e s t e d , r :e Q R S ~ : ' of i'ar.do LC LOW was found t o have no e f f e c t on the spanwise loading d i s t r . burio:: jrld rlw vc., t;lx crrrjec- t o r i e s . The chordwise loading is profoundly a l t e r e d t y elit7 C Y ~ ; % . :: + ' -7.' and can only be simulated by nonlinear aerodynamic techniya*:.a uhf: ', =*? , !v s, ,;~oc.kboundary l ayer interaction model.

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ACKNOWLEDGMENTS

This work represents the contributions of many excellent people. We would like to extend our thanks to W. D. Vann (Ft. Eustis Directorate, U.S. Army Applied Tech- nology Laboratory) and H. Jones (U.S. Army Research and Technoloey Laboratories) who were instrumental in initiating our computational studies. Special acknowledgment is due to Georgene Laub who tirelessly and ably assisted in the running of the test. Thanks also to M. Summa (Applied Mechanics, Inc.) who wrote the lifting surface code i,ind assisted us in running it; S. C. Lee (University of Missouri) and T. L. Holst ihes Research Center) who provided us with the finite difference computations.

REFERENCES

1. Crimi, P.: Theoretical Prediction of the Flow in the Wake of a Hovering Rotor. CAI. Report No. BI-1994-S-1 and No. BB-19944-2, Cornell Aeronautical Labora- tory, Inc., Buffalo, N. Y., Sept. 1965.

2. Landgrebe, A. J.: An Analytical and Experimental Investigation of Helicopter Rotor Hover Performance and Wake Geometry Characteristics. USAAMRDL Technical Report 71-24, Eustis Directorate, U.S. Army Air Mobility Research and Develop- ment Laboratory, Fort Eustis, Va., June 1971.

3. Landgrebe, A. J. ; Moffett, R. ; and Clark, D.: Aerodynamics Technology for Advanced Rotorcraft, Part 1. J. American Helicopter Soc., vol. 22, no. 2, Apr. 1977.

4 . Johnson, W.: A Lifting Surface Solution for Vortex I~duced Airloads and Its Application to Rotary Wing Airloads Calculations. Massachusetts Institute of Technology, Aeroelastic and Structures Research Laboratory, TR 153-2, Apr. 1970.

5. Kocurek, J. D.; and Tangler, J. L.: A Prescribed Wake Lifting Surface Hover Performhnce Analysis. Presented at the 32nd Annusl National Forum of the American Helicopter Society, preprint 1001, May 1976.

6. Summa, J. M.; and Clark, D. R.: A Lifting-Surface Method for Hover/Climb Loads. Presented at the 35th Annual Form of the American Helicopter Society, Washington, D. C., preprint 79-1, May 1979.

7. Caradonna, F. X . : The Transonic Flow on a Helicopter Rotor. Ph.D. Thesis, Stanford U., Stanford, Calif., March 1978.

8. Rabbott, J. P., Jr.: Static-Thrust Measurements of the Aerodynamic Loading on a Helicopter Rotor Blade. NACA TN 3688, Langley Aeronautical Laboratory, National Advisory Committee for Aeronautics, Langley Field, Va., Feb. 1956.

9. Scheiman, J.; and Kelley, H. L. : Comparison of Flight-Measured Helicopter Rotor-Blade Chordwise Pressure Distributions with Static Two-Dimensional Airfoil Characteristics. NASA TN D-3936, 1967,

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10. Brotherhood, P.; and Young, C.: The Heaeurement and Interpretation of Rotor Blade Pressures and Loads on a Puma Helicopter in Flight. Pferented at the Fifth European Rotorcraft and Powered Lift Mrcraft F o M ~ , Amtardam, The Netherlands, Sept, 1979.

11, Gray, R. B.; McHahon, H. M.; Sh.noyr K, R,; and 8-r, H. L.: Surfbca Preerure Measurements at Two Tipe of a Model Helicopter Rotor in Hover. NASA CP-3281, May 1980.

12. Sullivan, J. P.: Experimental Investigation of Vortex Ringe and Helicopter Rotor Wakes Using a Laser Doppler Velocimeter. D. S, Diaeertation, Massachusetts Institute of Technology, June 1973.

13. Bsllard, J. D.; Orloff, K. L.; and Luebs, A. B.: Effect of Tip Shape on Blade Loading Characteristics. Presented at the 35th Annual N~tional Forum of the American Helicopter Society, Washington, D. C., preprint 79-1, May 1979.

14. Landgrebe, A. J.; and Johnson, B. V.: Mearurements of Model Helicopter Rotor Flow Velocities with a Laser Doppler Velocimeter. Tech. Note, J. American Helicopter Soc., vol. 19, no. 2, July 1974.

15. Boatwright. D. W.: Measurement of Velocity Component in the Wake of a Full Scale Helicopter Rotor in Hover. USAAMRDL TR 72-33, Aug. 1972.

16. Cook, C. V.: The Structure of Rotor Blade Tip Vortex. AGARD CP-111, Sept, 1972.

17. Holst, T. L.: A Fast, Conservative Algorithm for Solving the Transonic Full- Potential Equation. AIAA Paper 79-1456, July 1979.

18. Lee, S. C.: Effect of Turbulent Roundary Layer on Transonic Flows. Preliminary Report, NASA Interchange Number NCA24R450-001, Aug. 1979.

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Page 35: Caradonna Tung

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Page 36: Caradonna Tung
Page 37: Caradonna Tung

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Page 38: Caradonna Tung
Page 39: Caradonna Tung

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Page 40: Caradonna Tung

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Page 41: Caradonna Tung

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Page 42: Caradonna Tung

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Page 43: Caradonna Tung
Page 44: Caradonna Tung

ORH31NAL PAGE IS OF 'POOR QUALIW

BLADE CONST RUCTtON C\ 7.5ft

HUB-SCANIVALVE ASSEMBLY

I 6 in. \ 143m) >

HOT W!RE WAgE TRAVERSE ,- I 120 in.

4 (3.068rn3

, WAKE EXHAUST DUCT '4

Figure 1.- The model and experiments1 set-up.

Page 45: Caradonna Tung

UPPER SURFACE UPPER SURFACE

LOWER SURFACE

I

/ 4

I

0 .5 1.0 0 .5 1 .o 0

xlc xlc

52 = 1750 rpm Mtip = 0.612

- 1 .,. UPPER SURFACE

R = 2250 rpm R = 2500 rpm Mtip = 0.794 Mtip = 0.877

- 1 ,/ UPPER SURFACE UPPER SURFACE

C~ LOWER SURFACE

0

1

0 I

.5 1.0 0 .5 1 .o xlc xlc

Figure 2.- Comparison of measured pressure distributions at r/8 = 0.8 from each blade; collective pitch Bc = 8' (solid line = right blade, open symbol = left blade).

Page 46: Caradonna Tung

figure 3.- Measured pressure distributions; collective pitch 8, - 5 ' .

Page 47: Caradonna Tung

L

------- $2 = 1250 rpm

MTlp 0.439 CT '0.00459

r/R = 0.80 --- R = 1750 rpm MTIP= 0.612 CT " 0.00455

- 5'2 = 2250 rpm MTlp= 0.794 CT = 0.00462

.5 1.0 --- $2 = 2500 rpm X/C M ~ l p = 0.877

CT = 0.00473

Figure 4 . - Measured pressure distributions; collective pitch 8, - 8'.

Page 48: Caradonna Tung

L

---a = 1250rpm

MTIP CT 0.00796

r/R = 0.80 -a -1750rpm 0.610

- 1 CT a 0.00807

---- 52 = 2279 rpm

MTIP' 0 ~ 7 9 ~ CT "0.00792

.5 1 .o x/c

-2 -

. r/R = 0.50 r/R = 0.68

C~ - 1

0 .5 1 .o x/c xlc -

Figure 5.- Measured pressure distributione; collective pitch 0, 12'.

Page 49: Caradonna Tung

TEST DATA, 8, = 8"

SZ = 1250 rpm, CT = 0.00460 0 !2 = 2050 rpm, CT = 0.00461 0 $2 = 2500 rpm, CT = 0.00464

REGION OF LOADING VARIATION DUE TO RPM CHANGES

0 .4 .6 .8 1 .O RADIAL STATION, r/R

Figure 6.- Ef fec t of r o t o r speed on blade span loading.

Page 50: Caradonna Tung

PRESENT TEST DATA, 0, = 12", MT QPe, r/R - 496

0 GRAY'S TEST DATA, Oc = 1 l.So, MT = 4260. r/R = 0.966

PRESENT TEST DATA, 8, = 5, MT = 0.226, r/R = 0.96

0 GRAY'S TEST DATA, Oc = 6.18', MT = 0.250, r/R = 0.966

x/c

Figure 7 . - Comparison of present resul ts with s ingle blade t i p loading data.

Page 51: Caradonna Tung

VOR1 EX SHEET I

'VORTEX TRAJECTORY

\ 4' (TOP VIEW)

PROBE-VORTEX CORE INTERSECTION POINT

/

Figure 8.- Typical wake probe data.

Page 52: Caradonna Tung

0 S2=650rpm A 52 = 1250 rpm

+ 52 = 2540,2414 rpm \

52 = 2250 rpm - CURVE FIT OF PRESENT DATA

P: --a

0 KOCUREK, TANGLER DATA, Cp0.0046

0 50 100 150 200 250 300 350 400 4% VORTEX AGE, JI,, &g

Figure 9 . - Wake geometry measurements for various rotor speeds and comparison with classical data; collective pitch Bc - 8".

Page 53: Caradonna Tung

0 50 100 150 200 250 300 350 VORTEX AGE, $,, deg

Figure 10.- Wake geometry for various pitch settings.

Page 54: Caradonna Tung

Figure 1 1 . - Typical - ~ r t e x velocity-time trace and 1/R curve f i t for various pitch se . t inga; vortex age = 50' (nominal), fi = 1250 rpm.

Page 55: Caradonna Tung

Figure 12.- Typical vortex ve1ocit::-time trace and 1/R curve f i t for various ~ i t c ! . se t t ings; vortex age = 200' (nominal), R = 1250 rpm.

Page 56: Caradonna Tung

Figure 13. Typical velocity-time trace and 1/R curve fit for vartous rotor speeds; collective pitch Bc = 8'. vortex age QV 50"-65'.

Page 57: Caradonna Tung

I I I I I I

0 .2 .4 .6 .8 1 .O RADIAL STATION, r1R

.5

.4

u" I--

5 - 0 . 3 - U. &

8 U

t - J J -2 a z 9 k

Y V)

Figure 1 4 . - Effect of vortex p o s i t i o n on loading computation.

TEST DATA 8, = 8", OR = 150 m/s (491 fpr), CT 0.0046 - MEASURED WAKE GEOMETRY, CT = 0.0048 ,,- VORTEX CONTRACTION REDUCED

BY 0.025 R, CT = 0.0047 AM1 LIFTING- SURFACE THEORY - REGION OF Cp VARIATION DUE TO WAKE

GEOMETRY CHANGES . . ..'.I _. . ..: .... . . .

-

Page 58: Caradonna Tung

TEST DATA 6, = 12". QR = 150 mls (491 fps), CT = 0.079 - --- A.M.I. CODE, USING MEASURED WAKE GEOMETRY, CT1 0.0083 - A.M.I. CODE, VORTEX CONTRACTION REDUCED BY 0.025 R,

CT = 0.0080 /@I\

I \

.3 1 I I I 1 J 0 .2 .4 .6 .8

RADIAL STATION, r/R

Figure 15.- Comparison of measured and computed loading.

Page 59: Caradonna Tung

TEST DATA, 6, = 5", a R = 150 mls (491 fps), CT = 0.0021

-- - MEASURED WAKE, A = 1.0, CT 0.0024 /-\

--- CONTRACTION REDUCED BY 0.02R /

A = 1.0, CT = 0.0025 - CONTRACTION REDUCED BY O.02R

A = 0.81, CT = 0.0023

i- C ---...---

.2 .4 .6 .8 1 .O RADIAL STATION, r/R

Figurc 1b.- Comparison of mec~sured and computcd loadlug.

Page 60: Caradonna Tung

O TEST DATA AT 0.8R MT = 0.877

a = 2.10° (FROM A M.I. CODE) 0-- FINITE DIFFERENCE

-1.0 CODE,INVISCID [T. HOLSTI - FINITE DIFFERENCE CODE WITH VISCOUS EFFECT

C~ 0

Figure 17.- Comparison of measured and computed chordwise pressure distribution.