Two Dimensional Tests of GA(W)-1 and GA(W)-2 Airfoils

8/12/2019 Two Dimensional Tests of GA(W)-1 and GA(W)-2 Airfoils

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Wichita State University Libraries

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Wind Energy Reports, no.1 Center for Energy Studies

Two Dimensional Tests of GA(W)-1 and GA(W)-2 Airfoils at Angles-of-Attack from 0 to 360 DegreesDale Satran and M.H. SnyderWichita State University


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WER-l

P6-IZ-06-0 l

Wind Energy Report No. 1

TWO-DIMENSIONAL TESTS OF GA W) lAND GA W) -2 AIRFOILS AT ANGLES - OF-ATTACK

FROM 0 TO 360 DEGREES

byDale Sat ran

ndMelvin H. Snyder

Wind Energy Labora toryWichi ta S ta t e Univers i ty


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BSTR CT

Tes t s of the GA W) - l and GA W)-2 a i r f o i l s were conductedin the 2- D t e s t sec t ion o f the Wichi ta S t a t e Unive r s i ty7 x 10 low speed wind tunne l to de te rmine the l t , drag ,and p i t ch i ng moment c oe f f i c i e n t s o f th e a i r f o i l s . The chordso f the aluminum models were s i x inches . Thg a i r f o i l s ~ rt e s t e d a6 t h ree Reynolds numbers: .37 x 10 .51 x 1 0 , and.67 x 10 , and a t angles o f a t t a c k from a to 360 degrees .Hyste res i s s tud ies were a l s o performed from nega t ive s t a l lto pos i t i ve s t a l l .


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INTRODUCTIONAs a p ar t of the cont inu ing wind energy re s earch programa t Wichi t a Sta t e Univer s i ty , a two - bladed wind tu rb ine was de s igned and b u i l t r e fe rence 1) . It became ev i den t , dur ing the

des ign process and during the c a l c u l a t i on of o f f - de s i gn pe r fo r ma nce , t h a t t he re i s a se r ious lack o f a i r f o i l da ta fo r lowReynolds numbers a nd fo r l a rge ranges o f angle o f a t t a c k .From the l imi ted da ta ava i l ab l e , it appeared tha t theGA(W)-l a i r f o i l would be a b e t t e r sec t ion for a windmil l blade

i.e., sho r t e r chord and l i g h t e r we igh t ) than the o l der sec t i ons . For t h i s reason , the wind t u rb in e , descr ibed in r e f e r ence I , was cons t ruc ted using a GA(W)-l a i r f o i l .In order to provide des i g n da t a fo r fu tu re wind tu rb ine

des igns , t e s t s have been conducted in the Walte r H. BeechWind Tunnel a t Wichita Sta t e Unive rs i ty . These t e s t s , r e por ted in t h i s r e po r t , were two-dimensional te s t s of th eGA(W)-l and GA(W)-2 a i r f o ils .

MODELS AND TEST PARAMETERSThe models t e s t e d were the GA(\ l)-l and GA \v) - 2 a i r f o i l s .


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s t a l l t o deep pos i t i ve s ta ll and back to deep nega t ive s t a ll.The models were t e s t e d a t th r ee dynamic pres su r e s , 8 , 18 and4 8 p s f . These da t a were t aken o n t he force b a l ance . Wakes urveys were a l s o pe r f ormed us ing a f i ve - t ube probe to measu rethe t o t a l pre s s u re varia t i o n th rough the wake (see f iqure 4) .

D T REDUCT I ON

Fo rc e d a t a were reduced by a compu t e r prog ram whi chc o r re c t e d the da ta fo r f l ow a ngu l a r i t y , so l i d b l ockage , wakeblockage , ho r i z on ta l buoyancy, and tu rbu lence as shown inthe Appe nd ix . Th e program r e fe rence 2) computed lift , drag ,p i t c h ing momen t abou t the qua r t e r chord , normal and a x i a l co e f f i c i e n t s fo r each angle o f a t t a c k . Drag da t a from thefo rce ba lance inc luded i n t e r f e r e nc e and t a r e d r ag for theend p l a t e s . The d i f fe rences between the drag da t a from theforce b a l ance and from the wake survey were removed by thep r og r a m f o r each model to y ie ld the a c t u a l drag o f the model .

Pres su re da t a f r om the f i ve tube wake survey p r obe werereduced i n t o ve l o c i ties whi ch were i n t e g r a ted by ano the r p ro gram to y i e l d drag o f the model only . The wake survey wast aken too f a r s ix inches) behind the model . Veloc i ty p ro f i l e s th rough the wake were very f l a t wh ich h inde red d e t e r


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REFERENCES1. Dunn C.H. and Snyder M.H.: A Proto type wind Genera torSys tem Supplying Energy to the Elec t r i c Ut i l i t y Grid ,University of Missouri-Rolla Energy Conference , RollaMO Octo be r 1975.2. Rot ramel , Bre iden t h a l , and Wen t z ; Compu t i ng Rout ines for

Ai r f o i l Sec t ion Wind Tunnel Data Reduct on , Ae r onau t ica lEngineer ing Depar tment Wichi ta S t a t e Univers i t y , June1973.3 . Wentz W .H. , J r ., a n d Seetharam H.C.; A Fowler FlapSystem fo r a High-Performance Gene ra l Av t on Air fo i l ,Paper no. 740365 S.A.E. Business Airc ra f t MeetingWichita Kansas April 1974.


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SYMBOLS

b a i r f o i l span d i s tance between end plates f t .C a i r f o i l chord f t .Cd sec t i on drag coe f f i c i en t D/qbcc l sect ion l i f t coef f ic ient L/qbcc rnc sect ion pi tch ing moment coef f i c i ent Mi /qbC 2To drag lb .

li t lb pi tch ing moment about the quarter-chord f t . l b .

q d 1 v2y n m ~ c pressure 2P p s . f .


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TABLE IPr inc ipa l Parameters fo r GA W) l Airfoi l

Reynolds Number . 37 x 106 51 x 106 67 x 106

c l = 0 0 a t a = 4 .2 4.3 4.4a = 0 0 a t c l = 47 50 52

c lmax = 1 35 1 39 1 430 / 1 0

Cdmin = ~ g e 0 102 . 0077L/Dm x = 66 69 76 . 16 86 . 27

a ta = 6 20 6 20 2 20


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T BLEPrincipal Parameters for GA W)- 2 Airfoi l

Reynolds Number .37 x 10 6 . . 51 x 10 6 .67 x 106

c1 0.0 a t a 4 .6 _4.7 _4.8a 0.0 a t c1 .50 .52 . 54

Clmax 1. 37 1. 42 1. 45Cdmin . 0122 . 0091 .0067

L/Dmax 66.65 84.44 87.6 4a ta 4 20 4.2 4 .2 0


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chord l ine

t i 0 .17

GA(WH Airfo il Coo dina lesUppe SUlfac e Lower Surface

XI' XI,0.00000 0.00000 0.00000 0.000000.00200 0.01300 0.00200 -0.009300.00500 0.02040 0.00500 - 0.013 800.012,50 0.03070 0.01 250 -0.020500.02500 0.041 70 0 .02500 -0 .026900.03750 0 .04965 0.03750 -0.03 1900.05000 0.05589 0.05000 - 0.035800.07500 O.06SSI 0.07500 - 0.()42100.1 0000 0.07300 o.looon 0.047000.12500 0 .07900 0 .12500 - 0.05 1000.15000 0.08400 0.15000 -0.054 00.17500 0 .08840 0.17500 -0.05700


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Figure 3. View Of 2 D Te t Sect ion From Downstream Of Model


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Two Dimensional Tests of GA(W)-1 and GA(W)-2 Airfoils