Reentry is one of the most critical stages of a space mission and requires accurate prediction to reduce dangers from overheating and large pressures. Purpose of this research is to numerically simulate a double ellipsoid configuration at hypersonic speeds, using high resolution, high order and low dissipative numerical scheme. An algorithm is developed consisting of modified four-stage Runge-Kutta method as temporal scheme, a non-dissipative 4th order central difference scheme as base scheme, and a filter obtained from nonlinear dissipation part of Davis-Yee 2nd order symmetric TVD (Total Variation Diminishing) scheme pre-multiplied with the ACM (Artificial Compression Method) switch of Harten. This reduces numerical dissipation and computational cost compared to existing shock-capturing schemes. A full 3D compressible Navier-Stokes code is developed, and validated using 3D Double Ellipsoid to determine extent of numerical dissipation reductioa Fully structured, 3D grid compressed in the near wall region is used. The reentry problem is used to validate the code. The free stream test conditions applied are M∞ = 4.94 with Reynolds number Re = 5.26 ×107 at attack angle α = 0° and M∞ = 8.02 with Re =1. 98× 107 at attack angle α =0° and 25°. The results are compared with existing experimental data, and are found to be in good agreement
Re-entry TVD shock-capturing 3d double ellipsoid Mach number Reynolds number hypersonic
Muhammad Yamin Younis Tawfiqur Rahman Muhammad Amjad Sohail Zaka Muhammad Zaw Naing Tun
School of Aeronautical Science and Engineering, Beihang University (BUAA),Beijing 100191, China School of Astronautics, Beihang University (BUAA),Beijing 100191, China School of Aeronautical Science and Engineering,Beihang University (BUAA), Beijing 100191, China School of Astronautics,Beihang University (BUAA), Beijing 100191, China School of Astronautics,Beihang University (BUAA),Beijing 100191, China