The Use Of The Shock Tube In The Production Of Uniform Fields Of Transonic And Supersonic Flow PDF Download

A shock tube is proposed in which the flow conditions between the shock wave and advancing interface are expected to range from low subsonic to moderate supersonic speeds. Furthermore, testing times of 10 msec or more are predicted, a time quite adequate for aerodynamic force measurements. The driven section in the proposed facility is large enough to accommodate large scale models. To test the feasibility of the proposed tube, a shock tube was assembled using a surplus 7-foot diameter vacuum tank as a driven section and 12-in. flanged pipe for the driver. A series of tests were performed to determine shock formation time and experimental testing time. The results of thest tests are reported.