Experimental Study on Aerothermal Heating Caused by Jet-Hypersonic Crossflow Interaction

Abstract

The present paper reports on the results of an experimental study on aerothermodynamic effects associated with the injection of a laterial jet into a hypersonic cross-flow around a generic missile model. This study intends to close the gap of missing reliable information on measured combined surface pressure and heat flux distribution on a missile configuration with laterial jet. The model consisting of a cone, cylindrical main body and a flare includes a single side jet hole. The model is made of a material with low thermal conductivity, in order to visualize the surface temperature distribution, i.e. heat fluxes. The surface temperature development on the model has been measured by IR thermography. Using this data the heat flux rate has been determined taking into account temperature-dependent material characteristics, assuming a semi infinite wall and the exchange of radiative cooling to the environment. Flow topology was analyzed using oil flow and Schlieren images and wall pressure distribution measurements. The experimental data show that the jet pressure ratio has a significant effect on the side jet flow topology and its interaction with the cross-flow. The influence of the angle of attack and the yaw angle on the pressure and heat flux distribution has also been measured clearly. Finally the effect of various side jet gas media on the flow interaction has been demonstrated with tests using argon and helium as a jet gas complementary to air.