Спектр сверхзвукового обтекания вокруг летательного аппарата с управляющими тормозными щитками

Abstract

The article presents the results of the study of the spatial flow pattern of the aircraft model, the study of the flow structure near the surface of the aircraft by experimental and numerical methods. Comparative materials for visualizing flows around a conical model with a stern control body – a flat end shield during supersonic flight in atmospheric pressure air are presented. The difference from the qualitative flow pattern according to experimental spectra at M≈4 and M≈5.5 lies in the presence, in addition to the formation of a breakaway flow zone in front of the shield, an oblique jump of the seal (from the point of separation of the flow) and a more intense direct jump of the seal, the possibility of the appearance of a flow separation zone induced by the shield on the side of the model surface opposite the shield, with the formation of an oblique jump of the seal. The efficiency of increasing the number of brake shields installed on the cylindrical-conical model is considered. The results of measurements of the dependence of the increments of the drag coefficient of the tested models on the area of the shields are presented.