Computation of Drag over Launch Vehicle Fairing Configurations by Using Viscous Modeling
The flow field analysis over various reentry probes and fairing configurations are studied numerically by solving time-dependent compressible two and threedimensional Navier stokes equations. The governing fluid flow equations are discretized in spatial coordinates employing a finite volume approach, which reduces the equations to semi-discretized ordinary differential equations. Temporal integration is performed using multi-stage Runge-Kutta time stepping scheme. A local time step is used to achieve steady state solution. The numerical simulation is carried out on structured grid without employing multi-block mesh arrangement. The numerical computation is carried out for free stream Mach numbers range of 1.2-5.9 and angle of attack up to 12 degree. The flow features around the fairing and reentry body are characterized by a bow shock, expansion fan and base flow region in case of fairing. The numerical scheme captures all the flow field features well such as bow shock, expansion fan and downstream recompression shock. A comparison is made between present numerical results and with the experimental and Datcom results and the comparison shows a good agreement between them. Drag coefficients for different geometries have been calculated by these simulations.
supersonic flow hypersonic flow semi vertex angle cone angle mach number angle of attack drag Reynolds number tip radius
Zaw Naing Tun Tawfiqur Rahman Zahid Maqbool Muhammad Afzal Zaka Muhammad M Yamin younis Muhammad Amjad sohail
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191,China School of aeronautical science and engineering, Beijing University of Aeronautics and Astronautics,B
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
468-471
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）