Some observations on maximum pressure rise across shocks without boundary-layer separation on airfoils at transonic speeds

Walter F. Lindsey, Patrick J. Johnston
naca-tn-3820
Nov 1956


An investigation of the two-dimensional flow along flat plates having rounded leading edges has provided additional information on shock-induced separation. The results indicate that laminar boundary layers can sustain the theoretical pressure rise for normal shocks without separating provided that the local Mach numbers are less than about 1.4.

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