The Numerical Simulation of Hypersonic Flow over the Space Launcher
The goal of this work is a numerical simulation of flow features over the launcher of monoblock scheme on hypersonic flight regimes. The numerical investigations fulfilled for perfect gas using twodimensional axisymmetric Navier-Stokes equations based on program package, developed in TsAGI. The axisymmetric problem was solved using grids of the following dimensions: 401x201 and 601x301. The calculations were performed at M∞=6. The grid verification was carried out. The location of bow shock wave depending on angle of attack was obtained. The regions of flow separation and attachment were detected. The distributions of heat flux and pressure along the launcher surface are obtained.
the launcher hypersonic flow axisymmetric Navier-Stokes equations
Palchekovskaya Natalia
Central Aerohydrodynamic Institute, 1 Zhukovsky Street, Zhukovsky, Moscow Region, 140180, Russian Federation
国际会议
The 8th Sino-Russia High-speed Flow Conference(第八届中俄高超声速流体力学研讨会)
上海
英文
96-97
2011-11-21（万方平台首次上网日期，不代表论文的发表时间）