A Flight Investigation of Laminar and Turbulent Boundary Layers Passing Through Shock Waves at Full-scale Reynolds Numbers (1953)
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NACA TN 5056 20 … .016 .012 Q/\ 0.nd. .008 6*/l .004 0 .2 .4 .6 .8 1.0 1.2 1.4 X/l Figure 8.- Comparison of the effect of shock waves on the houndary-layer characteristics at low and at high Reynolds numbers with turbulent boundary layer ahead of the shock wave. NACA-Langley - 12-7-53 - 1000
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