Investigation of a high-performance top inlet to Mach number of 2.0 and at angles of attack to 20 degrees

Donald J. Vargo, Philip N. Parks, Owen H. Davis
naca-rm-e57a21
Mar 1957


Several top-inlet configurations were tested on a body of revolution in the 8- by 6-foot supersonic wind tunnel at angles of attack from 0 to 20 degrees and at free-stream Mach numbers of 1.5 to 2.0. The effect on performance of the following variable was studied: throat bleed, ramp perforations, inlet approach surface, side fairing, fuselage fences, canopies, and a simulated 60 degree delta wing.

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