平板圧縮コーナーを過ぎる極超音速流における高空力加熱領域位置の簡易推定

概要

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A semi-empirical model to estimate the location of the region where high aerodynamic heating occurs due to shock-wave/laminar-boundary-layer interaction around compression ramps in hypersonic flow is presented. To develop the behavioral formula, the scale of upstream influence and the free interaction characteristic are examined numerically. A flat plate/ramp configuration is used in the study and the following is obtained. A parametric model to evaluate the effects of ramp angle, wall temperature, Mach and Reynolds numbers on the scale is developed. The deflection angle of a boundary layer edge is estimated using a free interaction similarity rule. All model coefficients required are defined from numerical results. It is shown that the predicted position agrees with experimental data available. Finally, limitations concerning the model are discussed.