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Measurement of profile drag on an airplane in flight by the momentum method. Part II (1930)
NASA Technical Reports Server (NTRS) · leaf 36
1.0.Ju Technical Memorandum B©ViS3 Figs. iO.til 0.3 (gp-g) a, — q b, p/q_=-0.1 °'2 , p/q 0.1 a oo 8 c, p/a -0 s> p/q 0.2 o * CO 50 co 0.1 0 Fig.60 Effect of second, integral on result at p = const, the maximum ordinate for the normal total pressure loop being 0.3 q-~ formal loop. … 0.10 0.20 0.30 (g0-g) max. _______ Fig.61 Ratio of second to first integral for normal (approximately triangular) and rectangular loops, plotted against maximum total pressure drop and static pressure.NASA Technical Reports Server (NTRS)
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