The Research reported herein consists of a combined experimental and theoretical investigation of the downstream phenomena associated with the gaseous film cooling of a slender blunted cone in a hypersonic flow. A numerical solution of the boundary-layer equations with initial conditions reflecting mass injection is utilized to obtain predictions of the behavior of the downstream laminar boundary layer. Experimental measurements of heat transfer to the surface of the 10 deg half-angle cone model are made at a Mach number of 8, stagnation temperature of 2000 R, and freestream Reynolds numbers varying between 10000 and 80000/in. Comparison of the heattransfer data with the theory indicates the existence of regions of nonlaminar flow over the surface of the model and has permitted identification of the point of onset of transition.
Boundary-layer transition on a film-cooled slender cone
Grenzschichtuebergang bei einem filmgekuehlten, schlanken Kegel
US Government Reports ; 1-10
1975
10 Seiten
Report
Englisch
Boundary-Layer Transition on a Film-Cooled Slender Cone
AIAA | 1976
|Boundary layer transition on a film-cooled slender cone
AIAA | 1975
|