Accession Number : AD0702169

Title :   SHOCK TUNNEL SIMULATION OF SURFACE PRESSURE FLUCTUATIONS ON TITAN III MODELS.

Descriptive Note : Rept. for Jan 65-Jan 67,

Corporate Author : AEROSPACE CORP EL SEGUNDO CALIF LAB OPERATIONS

Personal Author(s) : Ross,David H.

Report Date : 01 OCT 1969

Pagination or Media Count : 47

Abstract : 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 1:30 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 fD/U. (Author)

Descriptors :   (*LAUNCH VEHICLES, AERODYNAMIC NOISE), ASCENT TRAJECTORIES, TURBULENCE, TURBULENT BOUNDARY LAYER, ROCKET MODELS, SHOCK TUBES, AERODYNAMIC CHARACTERISTICS, VIBRATION, SHOCK(MECHANICS)

Subject Categories : Acoustics
      Ground Support Sys & Facil For Space Vehicles

Distribution Statement : APPROVED FOR PUBLIC RELEASE