MUCH has been said earlier concerning the scale effect on drag. A few words must be added on the scale effect on lift near the stall, for it is here that ordinary small‐scale wind tunnel tests may be very misleading. The curves of Fig. 9 show the maximum lift coefficient of two wing sections plotted against Reynolds number, and the difference of behaviour is at once apparent.
Relf, E.F. (1936), "Aeronautical Progress 1930–1936: A Review of Scientific Progress Given in the James Forrest Lecture", Aircraft Engineering and Aerospace Technology, Vol. 8 No. 7, pp. 185-193. https://doi.org/10.1108/eb030066
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