Internal waverider hypersonic inlet and design method for giving attention to internal and external flow performance

Abstract

The invention provides an internal waverider-derived high speed inlet considering both internal flow performance and external flow performance and a design method thereof. The structure of the high speed inlet consists of a contraction section, an insulation section or an expansion section, wherein the contraction section of the high speed inlet is characterized by adopting three-dimensional inward contraction of a smooth curved surface. High speed incoming flow forms a curved surface shockwave at the inlet to close the inlet completely so as to realize that the inlet 'rides' on shockwave without overflow completely. The design method is to carry out flow line tracing by using a specific non-axisymmetric internally contracted basic flow field as a base to obtain downstream flow surface according to the given inlet shape, thereby obtaining a three-dimensional moulding surface of the internal waverider-derived high speed inlet. The non-axisymmetric internally contracted basic flow field can be obtained through performing gradual change based on the prior revolution surface along a circumferential contracting surface, and arranging a cylinder with specific radius on the axes. The internal waverider-derived high speed inlet and the method have the advantages that external flow resistance can be reduced more while ensuring high quality of internal flow, wide range of working mach number, strong counter pressure resistance and other performances of the internal flow.

Description

technical field [0001] The invention relates to an internal waveriding air inlet capable of taking into account both internal and external flow performance and a design method thereof. The inlet port is very large in the supersonic air-breathing propulsion system (sub-combustion ramjet engine) with flight Mach number between 2.5 and 5 and the hypersonic air-breathing propulsion system (scramjet engine) with flight Mach number greater than 5. The role of improving the overall performance. It belongs to the technical field of inner waveriding air inlet design. Background technique [0002] After the climax of the pursuit of double 3 (flight speed three times the speed of sound, flight altitude 30,000 meters) in the history of aviation technology development, the development of high-speed flight technology has slowed down for a period of time. However, in the past ten years, high-speed flight has once again become the focus of aviation technology development, especially with ...

AI Technical Summary

Problems solved by technology

[0005] From the various high-speed inlet design schemes proposed by other researchers at home and abroad that have been reported so far, the REST inlet of the NASA Langley Research Center in the United States can be regarded as the best in terms of taking into account various technical requirements of the inlet. There is still a need to improve the technical indicators, especially in terms of both the high quality of the flow field inside the inlet and the low resistance of the outside flow.

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