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):

Report Date:

1969-10-01

Pagination or Media Count:

47.0

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 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

Subject Categories:

  • Acoustics
  • Ground Support Systems and Facilities for Space Vehicles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE