Title :
Application of higher order low dissipative scheme on hypersonic flow field using a minmod limiter
Author :
Sohail, Muhammad Amjad ; Chao, Yan ; Afzal, M. ; Maqbool, Zahid ; Younis, M. Yamin ; Naidu, Suresh
Author_Institution :
Dept. of Fluid Mech., Beijing Univ. of Aeronaut. & Astronaut., Beijing, China
Abstract :
The different shapes of reentry vehicle cone with different radii and cone half angle have been studied and verified with experimental data by using higher order low dissipative scheme of Harten and Yee. A code has been generated to simulate the flow at high Mach number and shock capturing technique has been used for the location of shock waves. The patterns of shock waves and aerodynamics performance have been studied as radius or angle of cone is changed and compared with available experimental data. The developed code by using a flux difference scheme is also validated for the same. Three different geometries with tip to base radius ratios have been simulated at Mach 5.9 at a wide range of angle of attack -4°,-2, 0, 2, 4, 6, 8, 10,12°.
Keywords :
Mach number; aerodynamics; aircraft; flow simulation; hypersonic flow; limiters; pattern formation; shapes (structures); shock absorbers; shock waves; Mach number; aerodynamics performance; flux difference scheme; hypersonic flow field; low dissipative scheme; minmod limiter; reentry vehicle cone; shock capturing technique; shock wave pattern; Computational fluid dynamics; Angle of attack; Base radius; Blunt Cone; Cone angle; Drag coefficient; Lift coefficient; Mach number; Tip radius; air density; dynamic pressure; pitching moment coefficient; velocity;
Conference_Titel :
Mechanical and Electrical Technology (ICMET), 2010 2nd International Conference on
Conference_Location :
Singapore
Print_ISBN :
978-1-4244-8100-2
Electronic_ISBN :
978-1-4244-8102-6
DOI :
10.1109/ICMET.2010.5598407
