Numerical simulation of hypersonic flow around an aerospace plane by parallel RANS based CFD

摘要

This paper deals with a numerical investigation on a complex geometry aerospace plane configuration with no tail fuselage and leaping triangle wing tip similar to HERMES of France. Two case of numerical simulation which including aerodynamic and aerothermodynamics characteristic. Including two case investigation Numerical simulation two cases were performed for performed for Mach number of 4.97(Re=1.3 X 107) at angles of attack from-5 deg to 20 deg and 8.04(Re=1.13 X107) at angles of attack from-5 deg to 18 deg using parallel Multi-block Structure NS solver. Also three different CPU number are used in the investigation. Comparisons method used between the aerodynamic characteristics and wind tunnel data verify the reliability of the numerical method used for simulating viscous flow around the aerospace plane. Numerical results show that the present method is an effective and powerful analysis tool to predict the hypersonic flow field around a complex geometry.