Hypersonic Aerospace Vehicle Leading Edge Cooling Using Heat Pipe, Transpiration and Film Cooling Techniques
Hypersonic Aerospace Vehicle Leading Edge Cooling Using Heat Pipe, Transpiration and Film Cooling Techniques
- New search for: J. M. Modlin
- New search for: J. M. Modlin
An investigation was conducted to determine the feasibility of using liquid metal heat pipe, transpiration and film cooling techniques to cool aerospace vehicle leading edge structures exposed to severe, transient hypersonic flight aerodynamic heating environments. A finite difference, numerical cooling model was developed and applied to an aerospaceplane wing leading edge section and to a scramjet inlet section. It was demonstrated that these cooling techniques are feasible.
Document information
Hypersonic Aerospace Vehicle Leading Edge Cooling Using Heat Pipe, Transpiration and Film Cooling Techniques
1991
132 pages
Report
No indication
English
Manned Spacecraft , Cooling , Leading edges , Film cooling , Heat pipes , Inlets , Liquid metals , Supersonic combustion ramjet engines , Transpiration , Wings , Hypersonic vehicles , Aerospace planes , Liquid cooling , Sweat cooling , Aerospace craft , Finite difference theory , Ramjet inlets , Theses
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