Abstract

At supersonic speeds, an under-expande d rocket exhaust jet produces a deflection of the external flow and generates a rise in pressure that communicates upstream through the surface boundary layer. For sufficiently large pressure ratios, the viscous layer separates some distance forward of the base and may seriously affect vehicle stability. The present investigation develops an integral method for predicting some of the main features of the nearfield interaction between the exhaust plume and the surface boundary layer. The analysis is not restricted to laminar flow and extends to turbulent interactions by utilizing a simplified eddy-diffusivity model. The method also applies to the interaction that occurs in the wake of inclined or asymmetric bodies, and results for the flow over a flat plate at angle of attack are given.

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