Higher Order Low Dissipative Scheme Limiters Comparison for Hypersonic Blunt Cone
The maturity of shock-capturing finite difference methods for hyperbolic conservation laws has been a rapidly growing area for the last three decade. The construction of efficient high order low dissipation numerical methods for nonlinear hyperbolic conservation laws has been the subject of much research recently. The objective of the present work is to discuss the applicability and limitation of different limiters for Harten-Yee TVD Scheme. Hypersonic flow over Blunt cone is solved for comparative study. In all test cases, the flow is laminar, hypersonic, and the conditions are such that the perfect gas assumption is sufficient to describe the thermodynamics. Comparison is made between numerical and available experimental results for aerodynamics characteristics (Drag, Lift and Pitching moment coefficient.) of blunt cone. Steady-state numerical solution for the unsteady Navier-Stokes equation of finite-difference form is obtained by using central difference and Harten-Yee Roe TVD Scheme. Roes approximate average state is used to calculate eigenvalues and eigenvector matrix.
hypersonic flow laminar flow limitersi reentry probe Navier-stokes Mach number Reynolds number
Muhammad Amjad Sohail M.Yamin Younis Tawfiqur Rahman Zaka Muhammad Zaw Naing Tun
School of aeronautical science and engineering, Beijing University of Aeronautics and Astronautics,B School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191,China School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
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
456-459
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）