Method for designing axial-symmetry pre-compression fore bodies with boundary layer displacing functions
A design method and a technology with boundaries, which are applied to the combustion of the intake port of the power plant, supersonic aircraft, aircraft parts, etc., and can solve the problems of short length, shock wave total pressure, loss, etc.
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[0066] In order to make the object, technical solution and advantages of the present invention clearer, the implementation manner of the present invention will be further described in detail below in conjunction with the accompanying drawings.
[0067] A method for designing a precompressed precursor of an axisymmetric aircraft with boundary layer displacement, comprising the following steps:
[0068] S1. Design pressure controllable flow field
[0069] The pressure controllable flow field designed in the present invention is a pressure controllable flow with external rotation axis symmetry, and the pressure controllable flow field is composed of a direct shock wave dependent flow field and a main compression flow field.
[0070] S1.1 Solve the conical flow field after the direct shock wave
[0071] The leading edge point 1 of the aircraft, the central axis of the aircraft 2, the far-field incoming flow condition 3, and the lip center point 4 are known. The far-field incoming...
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