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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 1983, Vol. 4 ›› Issue (3): 1-8.
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Fu Dexun
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Abstract: A one-step difference scheme for solving two-dimensional steady state Navier-Stokes equations is proposed to solve supersonic and hypersonic viscous interaction problems near the leading edge of a flat plate.The scheme is considered and analysed with a model equation.It has second order accuracy in space for steady state problems and its stability condition is improved.The scheme is much simpler in comparison with the commonly-used two-step predictor-corrector difference scheme for N-S equations and also convenient for programing.Two viscous interaction problems are solved with the proposed scheme.One of them is with parameters M∞=20,TwT0=0.06,Re∞L=4×108;the other is with M∞=3,Tw=T0,Re∞L=103.The solutions are valid throughout the boundary layer,shock-wave structure and inviscid core.The results were compared with experimental data in good agreement.Numerical solutions show that the non-slip conditions can be used for weak viscous interaction.The computed results are helpful to understanding the physical nature of interaction problems.
Fu Dexun. NUMERICAL SOLUTION OF HYPERSONIC FLOW NEAR LEADING EDGE OF FLAT PLATE[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1983, 4(3): 1-8.
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