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An integrated design method for adaptive boundary layer displacement and inward transition inlet of waverider precursor

A waverider precursor and air inlet technology, which is applied in the integrated design field of waverider precursor adaptive boundary layer displacement and internal diversion inlet, can solve problems such as hindering airflow inflow and propulsion system failure to work normally, and achieve The effect of improving aerodynamic performance and improving aerodynamic characteristics

Active Publication Date: 2022-04-12
NANCHANG HANGKONG UNIVERSITY
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Problems solved by technology

During the compression process, the front body section will produce a thicker boundary layer. Due to the existence of the boundary layer, low-speed and low-energy airflow will enter the propulsion system. system not working

Method used

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  • An integrated design method for adaptive boundary layer displacement and inward transition inlet of waverider precursor
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  • An integrated design method for adaptive boundary layer displacement and inward transition inlet of waverider precursor

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Embodiment Construction

[0029] The implementation of the present invention will be described in detail below with reference to the accompanying drawings and examples, so that the realization process of how to use technical means to solve technical problems and achieve effects in the present invention can be fully understood and implemented.

[0030] like Figure 1 to Figure 9 As shown, the integrated design method of the adaptive boundary layer displacement and internal transfer inlet of the waverider precursor is characterized in that it includes the following steps:

[0031] (1), design the close cone waveguide waverider, the close cone waveguide waverider is composed of the lower surface 12 of the waverider precursor and the upper surface 9 of the waverider precursor; the specific design steps of the close cone waveguide waverider are: design The shock wave curve 5 and the characteristic profile line 6 of the lower surface of the waverider precursor, the characteristic profile line 6 of the lower ...

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Abstract

The invention relates to an integrated design method of a waverider precursor adaptive boundary layer displacement and internal transfer inlet, comprising the following steps: (1) designing a closely-cone-guided waverider; (2) selecting a three-dimensional internally contracting basic flow (3) Design the inlet profile of the internal turning inlet with adaptive boundary layer displacement effect; (4) Generate the 3D internal turning inlet compression profile with adaptive boundary layer displacement , to obtain the structure of the internal turning inlet; (5) Design the connecting plate of the waverider precursor of the internal turning inlet, and complete the integrated design of the waverider precursor adaptive boundary layer displacement of the internal turning inlet. While retaining the advantages of the waverider precursor, the invention carries out the design of the hypersonic air inlets in the form of symmetrical connection on the lower surface of the waverider precursor, so as to effectively displace the boundary layer of the precursor and exert the high performance of the waverider precursor. At the same time, it can effectively improve the aerodynamic performance of the propulsion system, and finally provide a new method for the integrated design of hypersonic internal and external flow.

Description

technical field [0001] The invention relates to the field of integrated design of a waverider precursor and an air inlet, in particular to an integrated design method for a waverider precursor adaptive boundary layer displacement and inward transfer inlet. Background technique [0002] Due to the complexity of hypersonic flow, the integration of airframe / propulsion system has become one of the key technologies for hypersonic flight. In recent years, scholars at home and abroad have carried out a large number of researches on integrated design methods, mainly focusing on the integrated design of aircraft precursor and air inlet. The waverider with high lift-to-drag ratio performance is the preferred aerodynamic configuration for hypersonic flight, while the three-dimensional inwardly turning inlet with high compression efficiency and high total pressure recovery coefficient is the preferred target for inlet design. [0003] During hypersonic flight, the hypersonic airflow us...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C21/00B64D33/02B64F5/00
CPCB64C21/00B64D33/02B64F5/00B64D2033/0226B64D2033/026
Inventor 贡天宇李怡庆
Owner NANCHANG HANGKONG UNIVERSITY
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