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The variation of aerofoil lift and drag coefficients with changes in size and speed (1923)
NASA Technical Reports Server (NTRS) · leaf 8
110. .0564 '}i£onoplane RAF.6 .3010 2 .0554 J .6990 5 .0542 .77S2 6 .053S .4771 3 R.and If. No. 14*. ■Monoplane RAF. 6c .0532 .3010 2 .0605 .1761 L5 .0572'l .3010 2 *^|BlpIaneRAF-6. .5185 3.3 R.aiid it. No. 196. .2219 LOT ;0S32 J .3424 2.2 Propeller aerofoil: .0555 -.0531 .375 .0510 x/c-0.6 -.1239… … Fig. 2.—Corrections to L/D for scale effects. Reproduc- Fig. 1.—Correction to lift coefficient for scale effect. Re- tion of figure 20, B.A.O. A. R.&H. No. 450. production of figure 19, B. A. C. A. R. & 1£. Xo. 450.NASA Technical Reports Server (NTRS)
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