Numerical Simulation On The Compressible Flow Over A Body With Sharp Edge

The reentry technology plays an important part in the ongoing development of military and economy in the world. Mastering reentry technology is important not only for guiding the upper stages of expandable launch vehicles into safe trajectories back to Earth, but also for the development of future space transportation systems. The reentry vehicle is an important step for achieving the development of reentry technology. It tests and qualifies the reentry technologies and flight control algorithms under actual flight conditions.The aerodynamic shape of a reentry vehicle determines the severity, duration, and flight path of reentry experienced by the vehicle. One of the main focuses of research in reentry vehicle is on modifying the shape of the vehicle. The shape of vehicle with sharp edge is currently of great interest to reentry vehicle designers due to its aerodynamic characters such as low drag, high lift and flexibility in changing its moving directions. In this thesis, a numerical study on a two dimensional long body with sharp edge has been carried out using the finite volume method. It aims to investigate the aerodynamic performance of this sharp body in a compressible fluid flow.The main work is as follows:First, a two-dimensional flow field is theoretically estimated before the actual calculations are carried out and a simplified 2-D model is set up.Then,the software Fluent6.12 is used to simulate the supersonic 2-D flow field by solving the Navier-Stokes equation. The following numerical simulations are first performed for two different situations: (1) a supersonic upstream flow over a body with sharp edge at different edge angles; (2) the supersonic upstream flow with several different attack angles over the same body. The distinct flow structures with shock waves have been observed. The simulation results are analyzed and the interaction between the angle of sharp wedge and the upstream flow are demonstrated. It is observed that the drag force becomes larger as the attack angle increases and smaller as the Mach number grows.Finally, investigations on a more complicated turbulence flow using a k -ε algorithm at various Mach numbers are conducted. The simulation results are analyzed and the effects of the Mach number on the force coefficients are presented.The present study and findings are valuable references for the further study of this sharp body in hypersonic flows.