Abstract
An analytical method of predicting the flow properties in gap regions about control surfaces of re-entry vehicles has been developed. The method is particularly applicable to regions containing ablating surfaces. The analysis is based on a quasi-one-dimensional compressible flow solution including the effects of area change, friction, heat transfer, mass addition, and shocks. Wall roughness and boundary-layer transition effects also are included. The boundary conditions match the local upstream and downstream pressure, when appropriate, determine the upstream total temperature, and employ a steady-state mass and energy balance at the wall-gas interface. Equilibrium thermochemistry is assumed. The method is compared to static pressure and aerodynamic heating measurements obtained inside gap regions on nonablating models in hypersonic flow and shows reasonably good agreement. Additional solutions are shown to illustrate the effects of various flight parameters, wall roughness, and area change on ablating gap flow conditions.
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