Supersonic Interference Flow Along the Corner of Intersecting Wedges

Abstract

A corner body represented by two intersecting wedges is used as a model to study an interaction of plane shock waves in space.With supersonic flow of such body, each wedge provokes forming a shock wave, and they are intersected and interact in space. There are two types of wedge-provoked shock wave interaction: regular and more complex – Mach's.The author of the article has investigated the possibility of one or another type of interaction of shock waves in the corner body. The type of interaction depends not only on the intersecting shock waves, but also on the position of the intersection line in space.The technique is based on analytical relations for oblique shock. For calculating is used a principle of the vector decomposition of running-in velocity into two components: one is directed along the line of intersection of shock waves, and the other lies in the plane of the normal line of intersection. Initial coordinate system is rotated so that one of its axes is directed along the line of intersection, and the two others lie in a plane perpendicular to the line of intersection. This is called a plane of calculation. In the calculation plane there is a normal component of the velocity, which is used as an initial. The flow structure in this plane is identical to two-dimensional interaction of shock waves.The type of interaction is determined by the two-dimensional calculation. The solution is reduced to finding the flow parameters on both sides of the tangential discontinuity. The solution is illustrated by the shock polar in coordinates: a pressure ratio - flow deviation.The article presents a calculating diagram to determine the interaction type of shock waves.The article gives the downflow calculation results: interaction between the reflected shock wave and the wedge surface and other surfaces.Determining the type of interaction is necessary in calculation of such flows by numerical methods, since it allows proper defining the geometry of the computational domain. In addition, in the case of regular interaction the analytical formulas can be used to determine the reflected shock parameters thereby reducing the time of numeric calculations and increasing the accuracy. The developed algorithm can be used in designing the space input devices for high supersonic speed aircrafts.

Keywords

• shock waves interaction
• corner body