A limit pressure coefficient and an estimation of limit forces on airfoils at supersonic speeds

John P. Mayer
naca-rm-l8f23
Aug 1948


The results of an estimation of the limit forces on airfoils at supersonic speeds are presented. The value of the maximum lift coefficient obtained from this estimation decreased from about 1.13 to 0.96 in a Mach number range from 1.4 to 3.0.

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