EE FOR AERONAUTICS .0/00 Aft 0 ,w'^o / 2 3 4 s: a 7 a s - .... Camber, percent chord Figure 5.—Additional ACz> due to the effect of camber were plotted from data obtained in the variable density tunnel. The accuracy of these curves can be surmised by the scattering of points plotted; the error,… … Lift coefficient, Cx, Figure 6.—aCd0 vs. Cl at high Reynolds Numbers, one finds in support of Mr. Knight's suggestion that, as a simple approximation AC»0 = 0.0093 CL™5 (20) This holds true approximately for all normal-shaped sections. Hence, (21) and Ql'8 Total C„ = £^ + 0.0093 CL*M+^p-…
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