Abstract
An experimental study has been carried out to develop a subcritical flow model to predict the additive drag and stable flow range of two-dimensional external compression supersonic inlets. Two variable geometry inlet models have been tested in a 0.3-m trisonic wind tunnel at Mach number varying from 1.6 to 2.2. the inlet mass flow was varied in the steady subcritical flow range and the total pressure recovery, ramp pressure distribution and mass flow ratio were measured. The corresponding shock stand-off distance was obtained from schlieren pictures. Based on these experimental data, a new subcritical flow model that correlates the inlet geometry, shock stand-off distance, and freestream Mach number has been developed.
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