Inviscid and Viscous Computation on Aerodynamic Characteristics of A Conventional Projectile
In this research work the supersonic flows are simulated by using inviscid and viscous modeling. The inviscid flux vector is evaluated by standard upwind, flux vector-difference splitting. This approach acknowledges that flux vector contains characteristics information propagating through the domain with speed and direction according to eigenvalues of the system. Inviscid and viscous effects on cylindrical body with and without fins are described and discussed in detail. The numerical predictions include lift, drag and pitching moment coefficients at different angle of attacks and Mach number. Comparison of two geometries, cone cylinder and cone cylinder with fins is provided in order to study the effects on the aerodynamics characteristics by the addition of the lifting surfaces and the same is compared with the available experimental data. For the present study supersonic flow is simulated at Mach number 4 and the angle of attack is varied. First calculation are done on inviscid modeling and using Flux difference scheme of Roe which is first order accurate but limiters are used to get higher order accuracy and suppress the oscillations in high pressure gradient flows and in discontinuity regions. First order scheme produces oscillations and unstable solutions in discontinuities and shocks. Then results obtained from these inviscid calculations are under predicted so viscous turbulent modeling of K -ω SST model of Menter is used to capture the viscous and turbulence effect of flows. It was observed that inclusion of viscous effect increase the accuracy of the solutions and results have very good agreement with the experimental results. Roe TVD scheme and limiters are successfully implemented for supersonic flows and hyperbolic equations. Three different types of limiters are used here to get second order accuracy and to stable the solutions near shock and in discontinuous regions. Cone-cylinder body (with and without fins) is used for the above methodology to simulate the flows for inviscid and viscous flows and results for both these two cases are obtained at mach 4 and at different angle of attacks. The results have very good agreement with experimental results.
supersonic turbulent model mach number angle of attack drag coefficient shock waves roe scheme limiters hyperbolic equations
Muhammad Amjad Sohail Tawfiqur Rahman M Yamin Younis Zaw Naing Tun Zaka Muhammad Zahid Maqbool
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
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
460-463
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）