Pressure recovery, drag, and subcritical stability characteristics of conical supersonic diffusers with boundary-layer removal

Obey, Leonard T., Englert, Gerald W., Nussdorfer, Theodore J., Jr.
naca-rm-e51h29
1952


A study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone boundary-layer bleed was made on a 16-inch ram-jet engine in the Lewis 8- by 6-foot supersonic wind tunnel. A greater stable subcritical range of operation was obtained with the bleed inlets than with the corresponding inlet without boundary-layer bleed. The drag added by the bleed system was small.

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