Effects of secondary injection forms on thrust vector performance of shock vector controlling nozzle

By taking alterable specific heat ratio and effects of temperature on viscosity coefficient into account, based on CFD technology, effects of secondary injection geometric parameters, including injection angle and non-dimension slot width, on three dimensional flow characteristic and vector performance of shock vector controlling nozzle under different nozzle pressure ratios and secondary pressure ratios were investigated. Results show that, with increase of injection angle, position of main separation line before injection slot moves forward and shock angle ascends. In case of smaller secondary pressure ratio, thrust vector angle increases with the injection angle. When secondary pressure ratios equal to 1.0 and 1.2, there is an optimal injection angle for a maximal thrust vector angle. If non-dimension slot length is less than 1.0, the separation vortex before injection slot becomes into horse vortex and induces wake vortex. When secondary pressure ratio is larger than 0.6, thrust vectoring angle ascends with the increase of non-dimensional slot length.