Accession Number:

AD0292901

Title:

LAMINAR SEPARATION IN SUPERSONIC FLOW

Descriptive Note:

Corporate Author:

CENTRE NATIONAL D'ETUDES ET DE RECHERCHES AERONAUTIQUES BRUSSELS (BELGIUM)

Personal Author(s):

Report Date:

1962-09-30

Pagination or Media Count:

1.0

Abstract:

A preliminary experimental investigation was made of the effect of three-dimensional flow perturbations on the heat-transfer rate in the reattachment region of a laminar flow behind a two-dimensional backward-facing step. It was found that the mean value of the heat-transfer rate was increased by as much as 70 by the presence of strong flow perturbations, while the recovery factor increased approximately from the laminar value to the turbulent one. A novel technique of heat-transfer measurements was used, by which heat was uniformly dissipated on the surface of the model. A theory was developed for the case of a supersonic flow over a flat plate, which gives an exact solution of the boundary-layer equations when heat is uniformly dissipated on the surface. It was shown in particular that the ratio of the heat-transfer coefficient for an isothermal wall to the heattransfer coefficient for uniform heat-flux is a constant independent of Mach number and Reynolds number. Numerical integration showed that it is equal to 0.72, independently of the Prandtl number in the range 0.5 to 1.0. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE