Abstract
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.
Degree
MS
College and Department
Ira A. Fulton College of Engineering and Technology; Mechanical Engineering
Rights
http://lib.byu.edu/about/copyright
BYU ScholarsArchive Citation
Shumway, Rex W., "Heat Transfer in Shock Boundary Layer Interaction Regions" (1965). Theses and Dissertations. 7185.
https://scholarsarchive.byu.edu/etd/7185
Date Submitted
1965-8
Document Type
Thesis
Handle
http://hdl.lib.byu.edu/1877/Letd75
Keywords
Boundary layer, Aerodynamics, Heat, Film coefficients (Physics)
Language
English