Accession Number : AD0248344
Title : SOME ASPECTS OF SHOCK-WAVE GENERATION BY SUPERSONIC AIRPLANES
Corporate Author : ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE)
Personal Author(s) : JORDAN, G.H.
Report Date : SEP 1959
Pagination or Media Count : 19
Abstract : Various theoretical, wind-tunnel, and flight investigations conducted in regard to the flow fields generated by an airplane at super(over) sonic speed indicated that appreciable pressure disturbances can be imposed on the ground as a result of the shock waves extending to ground level. The pressure rise through the bow wave of an airplane in the far field is dependent on the over-all area development rather than on local details and can be estimated with some degree of confidence. Configuration details influence the flow field in the near field in that they determine the number, strength, and location of shocks. One of the simplest and most effective means of reducing the shock-wave intensity at ground level is to maintain adequate altitude in order to attenuate the shock-wave pressures to acceptable levels. Flying through the supersonic flow field of an airplane in a close-vicinity passing maneuver can result in appreciable airplane motion and load. Passing a subsonic airplane, or any case in which fast passing rates are involved, results in negligible airplane motion. (Author)
Descriptors : *GROUND EFFECT, *SHOCK WAVES, *SUPERSONIC FLOW, *SUPERSONIC AIRCRAFT, AERODYNAMIC CONFIGURATIONS, ATTENUATION, PRESSURE, STRUCTURES.
Distribution Statement : APPROVED FOR PUBLIC RELEASE