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- W210930319 abstract "Abstract : 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." @default.
- W210930319 created "2016-06-24" @default.
- W210930319 creator A5044295429 @default.
- W210930319 date "1963-02-18" @default.
- W210930319 modified "2023-09-24" @default.
- W210930319 title "A SHOCK TUBE FOR PRODUCING SUBSONIC, TRANSONIC, AND SUPERSONIC FLOWS FOR AERODYNAMIC TESTING" @default.
- W210930319 doi "https://doi.org/10.21236/ad0403045" @default.
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