TY - GEN
T1 - Effects of turbulence modeling on aerodynamic characteristics of a conventional tailed missile configuration
AU - Sohail, Muhammad Amjad
AU - Chao, Yan
AU - Yamin Younis, M.
AU - Afzal, M.
AU - Maqbool, Zahid
PY - 2010
Y1 - 2010
N2 - The performances of K-ω SST(Shear-Stress Transport) turbulence model and high order low dissipative Flux difference scheme of Roe are evaluated against experimental flow fields at different geometries and angle of attacks at supersonic mach no. The numerical predictions include lift, drag and pitching moment coefficients at different angle of attacks. Most significantly, this research provides a sensitivity study on the accuracy of the solutions with respect to the effects of free stream turbulence, grid resolution, grid spacing near the wall, initial conditions, numerical methods and free stream Mach number effects on compressible flows. 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.
AB - The performances of K-ω SST(Shear-Stress Transport) turbulence model and high order low dissipative Flux difference scheme of Roe are evaluated against experimental flow fields at different geometries and angle of attacks at supersonic mach no. The numerical predictions include lift, drag and pitching moment coefficients at different angle of attacks. Most significantly, this research provides a sensitivity study on the accuracy of the solutions with respect to the effects of free stream turbulence, grid resolution, grid spacing near the wall, initial conditions, numerical methods and free stream Mach number effects on compressible flows. 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.
KW - Drag coefficient
KW - Implicit and explicit
KW - Lift coefficient
KW - Pitching moment coefficient
KW - Turbulence
KW - Wake
UR - https://www.scopus.com/pages/publications/78649303221
U2 - 10.1109/ICMET.2010.5598414
DO - 10.1109/ICMET.2010.5598414
M3 - 会议稿件
AN - SCOPUS:78649303221
SN - 9781424481019
T3 - ICMET 2010 - 2010 International Conference on Mechanical and Electrical Technology, Proceedings
SP - 516
EP - 520
BT - ICMET 2010 - 2010 International Conference on Mechanical and Electrical Technology, Proceedings
T2 - 2010 International Conference on Mechanical and Electrical Technology, ICMET 2010
Y2 - 10 September 2010 through 12 September 2010
ER -