Appeal No. 95-4237
Application 07/887,002
boundary layer over the surface of a body of an aircraft in
flight from acquiring the thickness of which changeover into
turbulence can be produced (column 1, lines 44-48). To this
end, a series of rearwardly facing orifices 3 are provided in
the wing of the aircraft, which orifices communicate with one
of several hollow interior portions 12 (see Figures 8 and 9)
of the wing. Portions 12 are in fluid communication with the
low pressure or suction side of a blower 14 driven by a motor
15. The blower lowers the pressure in the hollow interior
wing portions 12 such that a portion of the boundary layer
flow is drawn off through each of the orifices 3. The blower
delivers the drawn off flow to a propulsion nozzle 17 oriented
in the opposite direction to that of the absolute velocity of
the aircraft. A plurality of independently adjustable hinged
flaps can be provided at the connection between each portion
12 and the blower so that the flow from the respective
portions can be independently varied.
Miller relates to “cooling of aerodynamically heated
surfaces,” and in particular to “surface cooling for infrared
signature reduction using a combination of pressure and
temperature induced phase change of a coolant from liquid to
-6-
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Last modified: November 3, 2007