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
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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