
Accession Number : AD0292901
Title : LAMINAR SEPARATION IN SUPERSONIC FLOW
Corporate Author : CENTRE NATIONAL D'ETUDES ET DE RECHERCHES AERONAUTIQUES BRUSSELS (BELGIUM)
Personal Author(s) : GINOUX,JEAN J.
Report Date : 30 SEP 1962
Pagination or Media Count : 1
Abstract : A preliminary experimental investigation was made of the effect of threedimensional flow perturbations on the heattransfer rate in the reattachment region of a laminar flow behind a twodimensional backwardfacing step. It was found that the mean value of the heattransfer 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 heattransfer 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 boundarylayer equations when heat is uniformly dissipated on the surface. It was shown in particular that the ratio of the heattransfer coefficient for an isothermal wall to the heattransfer coefficient for uniform heatflux 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)
Descriptors : *LAMINAR BOUNDARY LAYER, ATTACHMENT, DRAG, HEAT TRANSFER, METAL PLATES, MODEL TESTS, SUPERSONIC FLOW, THEORY, TURBULENCE, WIND TUNNEL MODELS
Distribution Statement : APPROVED FOR PUBLIC RELEASE