Aerothermodynamic characteristics of an associated body under conditions of supersonic flow

An experimental investigation is performed of the distribution of heat flux and pressure over the surface of an associated body located at different distances in the supersonic wake of another body. The results are given of an analysis of the effect of the connection of a pair of bodies on the pattern of flow and distribution of the above-identified parameters under conditions of symmetric and asymmetric flow. An increase in the perforation of an associated concave body to $5.3\%$ causes an increase in the heat flux on its inner surface for both schemes of flow between models both in the presence of a unified separation zone and in the presence of a pressure shock before the rear body. The results of this study enable one to estimate the aerothermodynamic characteristics of deceleration units using experimental or prediction data for associated bodies [1].