Accession Number:

AD0435813

Title:

INVESTIGATION OF SIMULATION OF SHOCK-SHOCK INTERACTION IN HYPERSONIC GASDYNAMIC TEST FACILITY,

Descriptive Note:

Corporate Author:

NORTH AMERICAN AVIATION INC COLUMBUS OHIO

Report Date:

1964-03-01

Pagination or Media Count:

63.0

Abstract:

An experimental investigation is conducted to determine the feasibility of laboratory simulation of the interaction of the shock wave of a hypersonic body with a separate moving shock wave. The experimental technique uses a blunted cone mounted in a hypersonic wind tunnel to generate the body shock wave. Shock tubes are used to generate the moving shock wave. The hypersonic tunnel is operated at Mach 7.3. The shock tube generates moving shock wave velocities from 3600 to 13,500 feet per second. The tubes are installed at angles of 30, 60, 90, and 120 degrees with respect to the tunnel centerline. Pressure measurements and Schlieren photographs are used to define the characteristics and the shock interaction. The Schlieren photographs show that the moving shock wave will move across the hypersonic stream and intersect the body. Transient pressures associated with arrival of the moving shock wave increase with increasing shock velocity. It is concluded that the technique investigated provides a feasible method for laboratory simulation of the interactions between a moving shock wave and a hypersonic body. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE