Accession Number:

AD0416150

Title:

HYPERSONIC FLOW OVER A YAWED CIRCULAR CONE.

Descriptive Note:

Hypersonic Research Project,

Corporate Author:

CALIFORNIA INST OF TECH PASADENA FIRESTONE FLIGHT SCIENCES LAB

Personal Author(s):

Report Date:

1963-06-30

Pagination or Media Count:

135.0

Abstract:

A 10 degree semi-apex, circular cone is tested in air at Mach 8 and at yaw angles to 24 degrees surface pressure, heat transfer, and pitot pressure throughout the flow field are presented. The nominal surface temperature is 40 of the free stream stagnation temperature, and the Reyn olds number, based on cone generator length, is varied from 0.5 x 10 to the 5th power to 4.2 x 10 to the 5th power. Heat transfer is measured at higher surface temperature ratios up to 56 and Reynolds numbers up to 7.3 x 10 to the 5th power by reducing the free stream stagnation temperature. All raw data consist of continuous circumferential distributions of each quantity and are included in a supplement. The surface pressure data are compared with the theories of Stone-Kopal and Cheng Reshotkos theory of heat transfer to the windward generator is compared with experiment. The probe data delineate the boundary between viscous and inviscid flow and determine the shape of the outer shock wave as well as the secondary shocks which appear in the flow field at large yaw. The probe data are sufficient to determine the flow field in the plane of symmetry and permit an approximate rep resentation of the Mach number profiles of the separated viscous flow in the leeward meridian plane beyond a moderate yaw angle. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE