Investigation of pressure recovery of a single-conical-shock nose inlet at Mach number 5.4

Bernstein, Harry Haefeli, Rudolph C
naca-rm-e53a12
April 06, 1953


An experimental investigation of the performance of a single-conical-shock diffuser was conducted at a Mach number of 5.4 and a Reynolds number based on model diameter of 375,000. Total-pressure recoveries of 13.7 and 13.1 percent were obtained at angles of attack of 0 degrees and 3 degrees, respectively. The corresponding kinetic energy efficiencies were 86.4 percent at an angle of attack of 0 degrees and 86.0 percent at an angle of attack of 3 degrees.

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