The NACA CYH airfoil section is described and its aerodynamic characteristics are given as tested in the NACA variable density wind tunnel at twenty atmosphere pressure. This section has a low drag, a high maximum lift, and a small travel of center of pressure

Higgins, George J

English

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I f 
I II IZ 52240 
TECHN I CAL NOTES 
JATIONAL A1' iJ I SORY COM1,OTTEE FOR AERONAUT I CS 
1;. / c2)/- ~ 7;1/' (f 
No . 240 
ThE N. A. C. A. CYH AIRFOIL SECT ION 
By Georg e J . Higgins 
Lan gley Memorial Aeronautical Laboratory 
Wash i U6t on 
J une, 1926 
q 
https://ntrs.nasa.gov/search.jsp?R=19930081042 2020-03-17T04:22:52+00:00Z
NOTICE 
THIS DOCUMENT HAS BEEN REPRODUCED 
FROM THE BEST COpy FURNISHED US BY 
THE SPONSORING AGENCY. ALTHOUGH IT 
IS RECOGNIZED THAT CERTAIN PORTIONS 
ARE ILLEGIBLE , IT IS BEING RELEASED 
IN THE INTEREST OF MAKING AVAILABLE 
AS MUCH INFORMATION AS POSSIBLE . 
l~ATIONAL ADVL30RY COl.J~ ITTZ:E FOrt AE:lm.AUT I CS . 
TEC~JICAL NOTE NO . 240 . 
THE N. A. C. A. CYE AIRFOIL SECTIOJ. 
By George J . Higgins . 
Summary 
The n. A. C. A. CYH airfoil section is descr i bed and its aero-
• 
dynam i c characteristics are z iven as tested in the N. A. C. A. var-
i [:.o le density wind tunnel at twenty atmospheres pressure . This 
section has a low d rag , a high maximum lift, and a small travel 
of center o~ pressure . 
The :1:J . A. C. A. CYE airfoil s ection was developed from the 
• Clark Y sect ion by modifying the aft er :port i on in such a manner 
that the center of pressure travel is reduced, mainta i ning as 
fur as 9 0ssible the good characteristics of the Cl ark Y section. 
Tll .-:; c~evelopmE.mt i s shown in Fig . 1 . The ordinates arc g iven 
in Table I . 
A nlaster of Paris ~odel airfoil was made and tested in the 
usua l manner i r.. thc var i c:ble density wind tunnel at a density 
cOI'rcs-==,onding to tvrenty a t::,I'Jospheres prcsrure . The results arc 
~iv8n in Table II and are plotted in Fi gs . 2 and 3 . The drag 
eOJff icicnt, moment coefficient ab out the quarter chord. :point , 
N. A. C. A. Technical Kot e ~o . 240 
niL va lue s , l111C_ the anGl es of attl1ck arc plotted a ga inst lift 
co-;ffic i cn t in Fi g . 2 ; a.nd the cente r of presGure aga inst lift 
coefficient in Fig . 3 . Thc drag is lov; the max i mum lift h i ·h; 
and the ccnter of pressure travel is small . 
CU1~CS of the minimum induced drag, the moment co eff ici-
ent a nd the lift coefficient as c~lculated fr om the present 
aerodynamic t heory arc also shown in Fi g . 2 f or comparison . 
The agr eement of the moment coeffic ien t curves i s very good . 
H. A. C. A. Technical Not e No . 240 3 
TABU: I. 
Chord line 
\( 
N. A.C .A. CYH AIRFOIL SECTI ON 
Ordinates in Fractions of Chord 
Sta . l.ooo . 0125 1025 . 050 l · 075 .10 ! .15 1·2~ . 30 ~;pe ~ - . 0;5~ ~-~~~~ I .~~~o -:-079 0 F08~-;;-~ 09601.10 68 5 ' . 1136 . 117 0 
L_O~~_~ ~:=t50 .0193 . ~~~ ' 00::±006~ ~~042_~001 5_ ...:0003...: 0~0 
Sta . . 40 . 50 . 60 . 65 .70 . 80 . 90 . 95 1. 00 
----f--- ----1---- -f---.-- - . ---- --
Uppcr . 1140 .10515/ . 09 1 5 . 08301 . 0741 . 0562 .0384 . 0293 . 0205 
Lower • 0000 I . 0000 , . 0000, . 0000 I· 00061 . 0038 . 0102 . 0140 . 0185 
Radius of leading cdge - 0.015. 
r 
, 
N. A. C. A. Techn i ca l Note No . 240 
T,,\.BLE II. 
Airfoil - N. 1.C . A. - CYH 
Avera ge t&nk pressure - 2 0 . 3 atm. 
Av e r age dynamic pressure - q=633 kg/m2 
Average Reynolds number - 3 , 570 , 000 
Ave r age temperatu r e - 330 C. 
I 
Angle Lift Drag 
of Coeffic i ent Coeffic i ent Rat i o 
attack 
d e grees CL CD D/ 1 
f--. 
- 6 - . 219 . 0158 - . 072 
- 4.5 - . 114 .0131 - .17 5 
- 3 . 002 . 0117 5 . 85 
-1 . 5 . 111 . 0114 . 103 
0 . 230 . 0133 . 058 
1 . 5 . 342 . 0 164 . 048 
3 . 454 . 02 17 . 048 
4 . 5 . 562 . 0279 ~ 05G) 
6 . 667 . 0351 . 053 
7 . 5 . 787 . 0458 . 058 
9 . 891 . 0554 . 062 
1 0 . 5 . . 989 . 0674 . 068 
1 2 1 . 096 . 08 19 . 075 
1 3 . 5 1 . 189 . 097 1 . 082 
1 5 1.267 . 1133 .090 . 
1 6 . 5 1 . 302 . 1310 
.
101 1 
18 1. 23 1 . 1989 . 161 
19 . 5 1. 196 I . 223 1 I 
. 187 
2 1 1. 066 . 2844 . 267 
I I , 
4 
Span - 30 in . (76 . 2 cm ) 
Chord - 5 in . ( 1 2 . 7 em) 
Aspect ratio - 6 
Material - Plas ter of 
Pa ris 
Date - J une 1 , 1926. 
Moment CEmter of 
Coeff i cient p ressure % 
chord 
CM ( . 25 cho rd ) f r om L. E. 
- . 026 1 3 . 0 
-. 034 - 5 . J. 
-. 031 1173 
-. 031 52 . 8 
- . 016 32 . 0 
- . 026 32 . 6 
- . 021 39 . 6 
- . 023 29 . 1 
- . 026 28 . 9 
- . 019 27 . 4 
- . 0 11 26 . 2 
- . 011 26 ~ 1 
- . 019 26 . 7 
- . 023 27 ~ 0 
- . 034 27 . 7 
- . 033 28 . 1 
-. 049 29 . 0 
- . 058 29 . 8 
- . 080 32 . 3 
..:. 
Line AB "!2.S clra-,r,m tp"ng8nt to upper c8.mber of the Clark Y section 
at A, 65% of tlle chcr~l. Line BD 'las drav:rn bisecting 2:1:::;13 L2C, T:-1e 
af t er part of the Clark Y section .,\EO vras then rotated. a.b out line ED 
2"S :tn axi s to th3 posi t ion CF A. ''lith the trp"i ling ec1 -:;e C11t to G·, 
making the chorJ 100%, the r evolved section bcca~e t~e after part 
of the modifi ad section, N.A.C.A. CYR. 
6510 Chord 
Ci R \T A.C. A. -, . 
' / ' / Chor
l 
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/ Clark Y d li '1c 
(r---- - - - - --~. ----~~~ QJ~ :-~B ~L 
I D"rl- -- - ---- --~ _~~ 1( _, 
--- , C' -- ____ IE 
/" _ _ -='0:'_ - --- A \ 
- -J -.,' __ n__ 100% Cho~d \ 
I 
Axis of rotation 
Fig . l De velopment of the N.A. C.A. eYB a irfoil section . 
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The NACA CYH Airfoil Section

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