GROUND MEASUREMENTS OF SHOCK-WAVE PRESSURE FOR FIGHTER AIRPLANES FLYING AT VERY LOW ALTITUDES AND COMMENTS ON ASSOCIATED RESPONSE PHENOMENA
Abstract
Extensive ground measurements of shock-wave pressure were made for two different supersonic fighter airplanes in the Mach number range of about 1. 05 to 1.16 and for altitudes from about 50 to 890 feet. Comparisons of the pressure rises across the shock wave measured on the ground are made with the available theoretical data, and these pressure data are correlated with some data on window-glass breakage. Brief discussions are also given relative to other associated phenomena such as ground motions and response of equipment and personnel. The pressure time histories measured at ground level were found to contain more peaks than would be obtained at ground level from flights at high altitudes. These pressure peaks seemed to be associated with features of the airplane geometry. The measured values of pressure rise across the bow shock wave decreased with increasing altitude as predicted by theory.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1961
- Accession Number
- AD0326913
Entities
People
- Domenic J. Maglieri
- Tony L. Parrott
- Vera Huckel
Organizations
- Langley Research Center