Experimental investigation of transverse jet interaction on a missile body using laser velocimetry and flow visualization

An experimental investigation of the interaction between a lateral jet issuing from a missile body and the oncoming external flow is presented. The experiments were carried out in the ISL supersonic blow-down wind tunnel at a Mach number of 3. The test model was a cone-cylinder-flare body with a side jet nozzle located on the cylindrical section, representing a simple generic high-speed missile configuration. For this study, three distinct flow conditions were chosen which are characterized by a jet ejection pressure ratio of 50, 70 and 97, respectively. Flow velocity measurements were performed with the aid of a two-component laser Doppler velocimeter (LDV). In addition, flow visualization techniques were used in order to confirm the LDV results. Combined with previous surface pressure measurements, the present investigation yields a consistent picture of the jet-induced flow field comprising a separation zone and various shock waves upstream from the jet exit. This detailed knowledge of the flow structure is required for evaluating the performance of lateral jet control systems