A Flight Investigation of Laminar and Turbulent Boundary Layers Passing Through Shock Waves at Full-scale Reynolds Numbers (1953)
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18 NACA TN 3056 … .3 .4 .5 .6 .7 X/C, (a) Mq = 0.710 + 0.002. (c) Mq = 0.759 ± 0.002. Figure 6.- Chordwise distribution of pressure coefficient P and boundary- layer characteristics 0, S*> H, and Rq for three values of free- stream Mach number with turbulent flow ahead of the shock wave.
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