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 mach r yf .80 b Density Kn mach c Temperature Kn mach d Mach No. Kn Mach .41 .25 e Wake streamline Kn Mach Fig. 15. Computed results of pressure density temperature Mach number and wake streamline for Kn 10-4 Mm . 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 ReD 2966 from Yang Hsu 1992 . The stagnation line profiles of density are shown in together with the DSMC results from Vogenitz etc. 1968 for two Knudsen numbers Kn 1 with the states of Mw 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 the solid line denotes the computed Kn results the symbols denote the DSMC results of Kn 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 .
