Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane IV : rectangular cowl inlets with two-dimensional compression ramps

Paul C. Simon
naca-rm-e52h29
Oct 1952


An experimental investigation was conducted to determine the performance of side inlets having external compression ramps and rectangular cowls mounted on the fuselage forebody of a proposed supersonic airplane. Compression-ramp angles of 6 and 12 degrees, simulating two positions of a variable-geometry inlet, were investigated at free-stream Mach numbers of 0, 0.65, and from 1.5 to 2.0 at angles of attack from 0 to 12 degrees. The air-induction systems were investigated with and without inlet cowl side fairing. Ram scoops were installed beneath the inlet ramps for removal of the fuselage boundary layer.

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