Abstract
Wind-tunnel measurements have been carried out in a scramjet inlet model at a freestream Mach number of 4.00. Measurements included velocity profiles using a two-dimensional laser Doppler velocimeter (LDV), Mach number surveys, skin friction measurements with Preston probes, wall static pressure distributions, density profiles with a laser holographic interferometer, and qualitative shadowgraph photography. The effect of boundary-layer bleed on the viscous flow entering the inlet was also investigated. It was determined that bleeding off the boundary layer increased the inlet efficiency substantially.
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