Performance characteristics of several types of axially symmetric nose inlets at Mach number 3.85

James F. Connors, Richard R. Woollett
naca-rm-e52i15
Nov 1952


An experimental investigation was conducted at a Mach number of 3.85 to determine the diffuser characteristics of a series of conventional axially symmetric nose inlets mounted on a 5-inch ram jet in the Lewis 2- by 2-foot supersonic wind tunnel. Performance evaluations of single-cone, double-cone, and isentropic diffusers were made in terms of total-pressure recovery and mass flow for a range of angles of attack from 0 to 10 degrees in addition, cowl pressure distributions were obtained at zero angle of attack.

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