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- W2356376653 abstract "The 3-D inner flow field of sidewall compression hypersonic inlet and the isolator is numerically studied by solving the 3-D Navier-Stokes equation.The RNG k-e model is used to solve the turbulence problem.And the analysis is mainly focused on the effect of the Mach number on the flow field.The static pressure distributions along the several special lines and the static pressure,Mach number contours on the characteristic surfaces are presented.According to the homogeneity of the parameters on the outflow section,it is more homogeneous for Ma=3 than for Ma=6.And the most air is compressed in the iso-wide contract tunnel between the front shoulder of the strut and the throat section of the inlet for Ma=6,while for Ma=3 the air is mainly compressed in the contract tunnel before the front shoulder of the strut.And the air is much more compressed for Ma=6 than for Ma=3.According to the cowl shock wave,it is stronger for Ma=6 than for Ma=3.And the inlet captured mass flow rate of Ma=6 is greater than that of Ma=3.It shows that the area near the sidewall and the corner zone between the sidewall and the top wall are the most probable subsonic zones." @default.
- W2356376653 created "2016-06-24" @default.
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- W2356376653 date "2002-01-01" @default.
- W2356376653 modified "2023-09-25" @default.
- W2356376653 title "Numerical Study of Mach Number at the 3-D Sidewall Compression Hypersonic Inlet and Isolator" @default.
- W2356376653 hasPublicationYear "2002" @default.
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