A buffering portion of boundary layer flow along a flight vehicle surface is diverted into an internal cavity at a downstream edge of a surface mounted window isolating recirculating flow of the diverted fluid through the cavity while it is cooled therewithin. Outflow of the cooled buffering fluid from at an upstream edge of the window is conducted into the buffering portion of the boundary layer flow to cool the window and prevent damage thereof by aerodynamically generated heating of the surface under high velocity flight conditions. Keywords: Patent applications; Air flow recirculation; Airfoils; Aerospace systems cooling; Windows aerodynamic heating. (EDC)
Window Cooling for High-Speed Flight
1990
9 pages
Report
Keine Angabe
Englisch
Patent applications , Trailing edges , Cooling , Internal , Flight , Boundary layer flow , Mounts , Mechanical Devices & Equipment , Aerodynamics , Leading edges , Aircraft , Aerodynamic heating , Cavities , Air flow , Surfaces , Buffers , Downstream flow , Airfoils , High velocity , Aerospace systems , Recirculation , Windows
Surface-protection and cooling systems for high-speed flight
Engineering Index Backfile | 1956
|SLUB | 1956
|Wiley | 2010
|AIAA | 1996
|Engineering Index Backfile | 1947
|