The interest in aerodynamic heating problems has been increasing rapidly in the last decade. This interest is no longer concentrated on the heating of simple shapes for which adequate heat transfer theory has been developed« Because of the increasing Mach number ranges of aircraft, the need for information on the aerodynamic heating of various components has become imperative. Only when the magnitude of the problem has been exposed can the design for reducing the severity of local heating be optimized. Definition of these problems is of interest, not only because of the flow phenomena, but because of possible design limitations of re-entry vehicles and supersonic aircraft inlets, wings, rudders, etc.
College and Department
BYU ScholarsArchive Citation
Shumway, Rex W., "Heat Transfer in Shock Boundary Layer Interaction Regions" (1965). Theses and Dissertations. 7185.
Boundary layer, Aerodynamics, Heat, Film coefficients (Physics)