SHOCK TUNNEL SIMULATION OF SURFACE PRESSURE FLUCTUATIONS ON TITAN III MODELS.
Rept. for Jan 65-Jan 67,
AEROSPACE CORP EL SEGUNDO CALIF LAB OPERATIONS
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An experimental investigation in The Aerospace Corporation low-speed shock tunnel was conducted for determination of the fluctuating pressure levels on the surface of Titan III models. This novel employment of the shock tunnel permits rapid and low-cost model testing and thus assists in the prediction of booster-vehicle acoustic environment. The configurations tested were 130 scale models of the Titan IIIA cone-cylinder core only and the Titan IIIC with both 120- and 156-in. -diam solid rocket motor boosters attached to the core. The electrical signals from the high-frequency, flush-mounted pressure transducers were digitized and then spectrally analyzed by a digital computer. The resulting model spectra were scaled for comparison with flight data on the basis of dynamic pressure q and Strouhal frequency fDU. Author
- Ground Support Systems and Facilities for Space Vehicles