Comparison of Performances of Flux Difference and Advection Upstream Splitting Method on Aerodynamic Characteristics of A Tail Finned Body Configuration
The performances of two schemes, flux difference by Roe and Advection Upstream Splitting Method AUSM schemes are evaluated against experimental flow fields at different mach numbers and results are compared with experimental data of supersonic with and without finned projectile. The turbulent model used here is SST model by Menter. The numerical predictions include lift coefficient, drag coefficient and pitching moment coefficient at different mach numbers and angle of attacks. Most significantly, this research includes a sensitivity study on the accuracy of the solutions with respect to the effects of turbulence, grid resolution, grid spacing near the wall, initial conditions, numerical methods and free stream Mach number effects on compressible flows. This work describes a computational study undertaken to compute the Aerodynamic characteristics of cone cylinder with and without fins using a structured Navier-Stokes computational technique. The geometrical models and all test conditions are given in the references. The CFD code bases on the idea of upwind scheme for the convective (convective-moving) fluxes. CFD results for cone cylinder tail fined missile calculated on above mentioned turbulence model are compared with the available data. Wide ranges of Mach number from supersonic to hypersonic speeds are simulated and results are compared. When the computation is done by using viscous turbulence model the above mentioned coefficients have a very good agreement with the experimental values. It was seen that SST model is most suitable even with low quality mesh on sharp corners. Roe scheme and AUSM scheme are very efficient in the regions of very high pressure gradients like shock waves and discontinuities.
Roe schemes AUSM schemes Turbulence Models Mach number Supersonic flows Sock wave and Discontinuity pressure gradients Finite volume Discretizations Explicit and implicit solver
Muhammad Amjad Sohail Zaka Muhammad M.Yamin Younis Zaw Naing Tun Tawfiqur Rahman Muhammad Afzal
School of aeronautical science and engineering, Beijing University of Aeronautics and Astronautics, 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
363-366
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）