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Tham khảo tài liệu 'advances in spacecraft technologies part 9', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | 310 Advances in Spacecraft Technologies a Pressure Kn 0.0001 mach 1.8 r yf 0.28 .80 b Density Kn 0.0001 mach 1.8 c Temperature Kn 0.0001 mach 1.8 d Mach No. Kn 0.0001 Mach 1.8 .41 .25 e Wake streamline Kn 0.0001 Mach 1.8 Fig. 15. Computed results of pressure density temperature Mach number and wake streamline for Kn 10-4 Mm 1.8 . 311 Gas-Kinetic Unified Algorithm for Re-Entering Complex Flows Covering Various Flow Regimes by Solving Boltzmann Model Equation Fig. 16. Continuum Navier-Stokes solutions past cylinder for Mz 1.8 ReD 2966 from Yang Hsu 1992 . The stagnation line profiles of density are shown in Fig.18 together with the DSMC results from Vogenitz etc. 1968 for two Knudsen numbers Kn 1 0.3 with the states of Mw 1.8 Pr 1 Tw T0 1. Here the space grid system used is 41X 35 and the modified Gauss-Hermite quadrature formula with 32 X 16 discrete points was employed. In Fig.18 the solid line denotes the computed Kn 0.3 results the symbols denote the DSMC results of Kn 0.3 the dashed line denotes the computed Kn 1 results and the symbols A denote the DSMC results of Kn 1. In general good agreement between the present computations and DSMC solutions can be .
