Shock tunnel measurement of the interaction amplification factor for a hot gas side jet in a supersonic cross flow

Abstract

An efficient method for the steering of bodies flying at high Mach numbers is the lateral jet control. Compared to fins, no drag is induced when the jet is inactive and there is no risk of aerothermal problems. Additionally, conventional fins are quite inefficient at high altitudes due to the low stagnation pressures. A disadvantage of the lateral control jet, however, is the complex flow pattern that is formed around the active jet. In front of the lateral jet, a bow shock in conjunction with a separation shock is formed. Behind the jet, a wake with a low-pressure zone exists (Fig. 1). In addition to the jet thrust, an aerodynamic force resulting from the flow interactions around the jet is acting on the body, which makes an accurate side force prediction very difficult. It is common to define an interaction amplification factor that takes into account both types of forces: the jet thrust as well as the interaction force.