EXPERIMENTAL INVESTIGATION OF ASYMMETRIC NOZZLES FOR ADVANCED HYPERSONIC SPACE PLANES - STRUCTURE OF NOZZLE JETS AND THRUST VECTOR CONTROL

Optimization of thrust and optimized integration of the nozzle into th e space plane are required under hypersonic flight conditions. The mai n flow characteristics of such nozzles are presented in form of an exp erimental parametric study. The individual variation of the parameters is quite inefficient for minimizing all drag producing phenomena like dead water regions at the base or flow separation at the nozzle wall. Here, a nozzle will be presented where the base drag can be reduced w ith the help of a bypass nozzle which, furthermore, allows an active t hrust control of the main nozzle flow.