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II IZ 52240
I TECHN I CAL NOTES JATIONAL A1' iJ I SORY COM1 , OTTEE FOR AERONAUT I CS
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No . 240 ThE N. A. C. A. CYH AIRF O IL SECT ION By Geor g e J . Hi gg ins Lan g ley Memorial Aeronautical Laboratory Wash i U6t on J un e, 1 92 6
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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 airfoi l 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 press ure . This section has a low d ra g , a high maximum lift, and a small travel of center o~ pressure .
T he :1:J . A. C. A. CYE airfoil s ection was developed from the
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Clark Y sect ion by modifying the aft er :p ort 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~eve lopmE.m t 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 . Th e drag eOJff icicnt, moment coefficie nt ab out the quarter chord. :p oint , N. A. C. A. Te chn ical K ot e ~o . 240
niL va lue s , l111C_ the anGl es of attl1ck arc p lotted a ga inst lift
co-;ffic i cn t in Fi g . 2 ; a.n d th e cente r of pre sGu re aga in st lift coefficient in Fig . 3 . Thc dra g is lov; the max i mum lift h i · h; and the ccnter of pressure travel is small .
CU1~CS of the m ini mum induced drag, the moment co e ff ici- en t a nd the lift coefficient as c~lculated fr om the pre sen t aerodynamic t h eory arc also shown in Fi g . 2 f or comparison .
T he ag r eem ent of the moment coeffic ie n t c urves i s very go od .
H. A. C. A. Technical N ot e No . 240 3 TABU: I.
Chord line
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N. A.C . A. CYH AIRFOIL SECTI O N Ordinates in Fractions of Chord
Sta . l. ooo . 0125 1025 . 050 l · 075 .1 0 ! .15 1·2~ . 30
~;pe ~ - . 0;5~ ~-~~~~ I .~ ~~o -:-079 0 F08~-;;-~ 09601.10 68 5 ' . 1136 . 117 0
L _ O ~~_~ ~:=t50 .01 93 . ~~~ ' 00::±006~ ~~042_~00 1 5_ ...:0003...: 0~0
Sta . . 40 . 50 . 60 . 65 .7 0 . 80 . 90 . 95 1. 00 ----f--- ----1---- -f---.-- - . --- - -- Uppcr . 1140 .10 515/ . 09 1 5 . 08301 . 074 1 . 0562 .0384 . 0293 . 02 05
Lo wer • 0000 I . 0000 , . 0000, . 0000 I· 1 . 0038 . 0102 . 01 40 . 0185
Radius of leadin g cdge - 0.015.
N. A. C. A. Techn i ca l No te No . 240 4 T ,,\.BLE II.
A irfoil - N. 1.C . A. - CYH Span - 30 in . (76 . 2 cm ) A vera g e t&nk pressure - 2 0 . 3 atm.
Chord - 5 in . ( 1 2 . 7 em) Av e r age dynamic pressure - q=633 kg/m Aspect ratio - 6 A verage Reynolds number - 3 , 570 , 000 Materia l - Pla s ter of P a ris Ave r age temperatu r e - 33 C. Date - J une 1 , 1926.
I CEmter of A ngle Lift Drag Moment p ressure o f Coeffic i en t Coeffic i ent Rat i o Coeff i cient
%
chord attack L. E.
D/ 1 CM ( . 25 ch o rd ) f r om d e grees CL CD ..:.
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1 3 . 0 - 6 - . 219 . 0158 - . 0 72 - . 026 .013 1 - .1 7 5 - 5 . J.
- 4.5 - . 114 -. 034 . 0117 5 . 85 11 73 - 3 . 002 -. 03 1 . 0114 . 103 52 . 8 -1 . 5 . 111 -. 031 32 . 0 0 . 230 . 0133 . 058 - . 016 32 . 6 1 . 5 . 342 . 0 1 64 . 048 - . 026 39 . 6 . 454 . 02 17 . 048 - . 02 1 29 . 1 4 . 5 . 562 . 0279 ~ 05G) - . 023 28 . 9 6 . 66 7 . 035 1 . 053 - . 026 27 . 4 7 . 5 . 787 . 0458 . 058 - . 0 19 26 . 2 . 891 . 0554 . 062 - . 0 11 . 0674 . 068 - . 01 1 26 ~ 1 1 0 . 5 . . 989 . 075 - . 01 9 26 . 7 1 . 096 . 08 19 1 2 . 082 - . 023 27 ~ 0 1 . 189 . 097 1 1 3 . 5 .090 . 2 7 . 7 1.26 7 . 1133 - . 034 1 5 28 . 1 . 1310 101 - . 033 1 6 . 5 1 . 302 . 1 29 . 0 . 1 61 -. 049 1. 23 1 . 1989 29 . 8 . 223 1 . 187 - . 058 19 . 5 1. 196 . 267 32 . 3 1. 066 . 2844 - . 080 2 1
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