A method for determining outer boundary of computational domain for numerical solution of steady flow around aircraft
A technology for numerical solution and determination method, applied in computing, instrumentation, electrical and digital data processing, etc., can solve the problems of computational grid waste, influence, and large selection of computational domain, so as to improve efficiency, reduce grid volume, and reduce Effects of Computational Fields
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[0037] The specific implementation manner of the present invention will be further described below in conjunction with the accompanying drawings. The process flow of the flow field initialization method for the numerical solution of the steady flow around the aircraft proposed by the present invention is as follows: figure 1 As shown, the method includes the following steps:
[0038] S1: Initially determine the outer boundary of the calculation domain and divide the grid:
[0039] Taking the standard model "AGARD HB-2" (Reference: Hypersonic Wind Tunnel Aerodynamic Test Method [Standard].GJB4399-2002.2002) as an example, its appearance is as follows: figure 2 shown. The input conditions for the numerical solution of the steady flow around it are: (1) the Mach number M of the incoming flow ∞ =7, pressure p ∞ =3000Pa, temperature T ∞ = 288.15K, angle of attack α = 10°, angle of sideslip β = 0° as an example; (2) The viscous model is the S-A model, and the wall boundary con...
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