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Integrated design method for adaptive boundary layer displacement and inward rotation air inlet channel of waverider

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 Improved aerodynamic performance and improved aerodynamic characteristics

Active Publication Date: 2021-07-13
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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  • Integrated design method for adaptive boundary layer displacement and inward rotation air inlet channel of waverider
  • Integrated design method for adaptive boundary layer displacement and inward rotation air inlet channel of waverider
  • Integrated design method for adaptive boundary layer displacement and inward rotation air inlet channel of waverider

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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] Such as 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 low...

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Abstract

The invention relates to an integrated design method for an adaptive boundary layer displacement and inward rotation air inlet channel of a waverider. The integrated design method comprises the following steps of (1) designing an osculating cone-derived waverider, (2) selecting the position of a three-dimensional internal contraction basic flow field, and completing the design of the basic flow field, (3) designing an inlet molded line of the inward rotation air inlet channel with a self-adaptive boundary layer displacement effect, (4) generating a self-adaptive boundary layer displacement three-dimensional inward rotation air inlet channel compression molded surface to obtain an inward rotation air inlet channel structure, and (5) designing an inward rotation air inlet channel waverider front body connecting plate, and completing the integrated design of the waverider front body self-adaptive boundary layer displacement inward rotation air inlet channel. The design of the hypersonic air inlet channel is developed on the lower surface of the waverider in a symmetrical connection mode while the advantages of the waverider are reserved, so that a forebody boundary layer is effectively removed, the aerodynamic performance of a propulsion system is effectively improved while the high performance of the waverider is exerted, and finally, a new method is provided for hypersonic speed internal and external flow integrated design.

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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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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