Window Cooling for High Speed Flight.
Patent, Filed 27 Apr 90, patented 14 May 91,
DEPARTMENT OF THE NAVY WASHINGTON DC
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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 there within. 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.
- Fluid Mechanics