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Aviation History
1938
1938 - 0266.PDF
SUPPLEMENT TO FLIGHT * 066 THE AIRCRAFT ENGINEER JANUARY 27, ](,'38, 013 012 Oil 010 0 0 O 009 oos 007 006 FIG.I 1I LAWS TO CURVES , .„ CB • 0 006OS tO 74 tz8s - C0o, 0-0054 + 0-00357t+O- 1 1 | > OTesr Resuirs I 5806 t* • L j A / 1 —• ^> / • / / / / / l/f / DRAG OF SYMMETRICAL AEROFOILS AT REYNOLDS NUMBER = 8 X I06 / • 0-8 -10 3 4 5 « 7 8 9 I •14. -16 18 -20 MAX. THICKNESS fc * CHORD -Cmo X 10* 2 3 4 5«H!I •22 . -24 -26 30 40 •005 •004 •003 oeu •002 •OOI 0 ( • • • u I i & a 15 •3 12 B / no SHIES O MAX. CAMBER AT -1* A M • " " 3 B • • .4 + - • - -7 THE FIGURES BESIDE EA< POHJT REPRESENT THE PERCENTAGE THICKNES FIG.6a c >S •02 r 10 9 8 7 6 AN, "% 4 3 1 0 9 FIG.2 ** 10 1\* 1 CDO, Cofej / * I 1 / RN RN ;)U" 1-2 1 11 ff- 1 1 80 n M 56 48 M) 32 24 16 8 0 AEROFOILS HAVING CENTRELINE FORMED OF TWO PARABOLIC CURVES + DITTO FORMED Of A STRAIGHT LINE AND A PARABOLIC ARC 02 04 06 08 . 10 a 14 16 18 1-0 a i 6 T .? o( / r 1 ! | | 1 i • 1 1 •i 1 —1—|— ! T 1 1! O POINTS FOR TO CHORD i ! 4 i 1 ! i ';;""* 2>. THICKNESS !ATK) ONLY ; i I •5 i i •i i FIG.4 s< •» — 10 .POSITION OF MAXIMUM CAMBER :N TERMS OF THE CHORO e i i t X FIG. 5 o X 06 08 10 tt H -16 18 20 THICKNESS/CMORD RATIO • C 22 24 FIG.7 PREVIOUS CURVES SECTION $518 ONLY SECTIONS 4309 4318 4509 6309 6316 J SECTIONS 4518 and 6509- WERE INTERMEDIATE: I Z AA 7 CLopr •3 -4 -5 6 -7 •f CL -CLeft - CLm-CLoi>r J-J—LJ9 1-0
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