Experimental investigation of side-jet steering for supersonic and hypersonic missiles

Abstract

An experimental investigation of the interaction between a side jet and the external flow is presented. The experiments were carried out in three different wind tunnels at supersonic and hypersonic Mach numbers ranging from 2 to 10. The model used in all the experiments consisted of a cylindrical body and various ogival nose sections, and had no lifting surfaces. The single sonic jet nozzle was located on the lee side of the cylindrical center body section with respect to a positive angle of attack. Several nozzle shapes and jet injection angles were examined. Forces and moments were measured directly in all the experiments, and surface pressure surveys were taken in some supersonic experiments. The results reveal a small jet force amplification at supersonic and hypersonic Mach numbers around zero angle of attack. Significant amplification because of positive angle of attack was noted at hypersonic speeds. The injection nozzle shape and vector angle can have a noticeable effect on the magnitude of the jet force amplification, especially at hypersonic speeds. In addition, the interaction gives rise to a significant pitching moment that may be utilized to produce an additional aerodynamic control force.