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.
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
Transpiration cooling in hypersonic flight
NTRS | 1989
|Transpiration Cooling in Hypersonic Flight
NTIS | 1989
|