Method for reducing heat flow rate of local reverse overflow of aircraft

Abstract

The invention discloses a method for reducing heat flow rate of local reverse overflow of an aircraft. The method comprises that normal temperature liquid overflows from the surface of a local high heat flow zone of the aircraft, and the liquid forms a thin layer on the high heat flow zone to cover the surface of the local high heat flow zone of the aircraft, so that the heat flow rate of the surface of the local high heat flow zone is reduced. According to the method, the normal temperature liquid continually overflows the surface of the local high heat flow zone of the aircraft, and under the condition that the aircraft flies at a high speed, the liquid forms the thin layer on the surface of the local high heat flow zone; the flow quantity of the overflowing liquid is a little, the area of the thin layer formed on the surface is small, and the thin layer mainly covers the local high heat flow zone, so the main flow of the aircraft is almost not disturbed, and the continual overflow can play a good role in reducing the heat flow of the local high heat flow zone. The method is particularly suitable for the sharp conical head of the aircraft with high lift-drag ratio.

Description

technical field [0001] The invention relates to a method for reducing heat flow rate by partial reverse overflow of an aircraft. Background technique [0002] The earliest studies on flood cooling were tangential jets to form a film to reduce the heat flow. In 1946, Wieghardt conducted research on hot air deicing to solve the problem of wing icing. In 1966, Goldstein et al first carried out experimental research on tangential sonic jet flow in Ma=3 supersonic flow. In 1970, Parthasarthy and Zakkay performed an experimental study on the near-tangential injection of different refrigerants (helium, hydrogen and argon) in the mainstream of Ma=6. From 1970 to 1971, Cary and Hefner conducted experimental research on flat film cooling in the mainstream of Ma=6, and the refrigerant was air. [0003] Their research found that the film cooling effect of Ma=6 supersonic flow is significantly higher than that of subsonic and Ma<6 supersonic flow under the same injection structure,...

AI Technical Summary

Problems solved by technology

It is found that the pressure ratio of plasma injection is under certain circumstances, although the momentum is smaller than that of cold flow injection, but the drag reduction effect is much greater than that

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