SHOCK TUNNEL SIMULATION OF SURFACE PRESSURE FLUCTUATIONS ON TITAN III MODELS.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1969
- Accession Number
- AD0702169
Entities
People
- David H. Ross
Organizations
- The Aerospace Corporation