Numberical Study Of Aeroheating For Hypersonic Reentry Bodies

High speed,far range,great military and economic potential make the hypersonic vehicle be one of the representatives of the development direction of future aerospace field. Aerodynamic heating problems are the key to the design of hypersonic vehicle TPS (Thermal Protection System). Numerical simulation is an important means of studying aerodynamic heating problems.Researching on the aerodynamic heating simulation has important significance.There are many research results at present,while less on the grid construction methods and bottom grid scale, moreover, model is relatively simple,something may be wrong when extending method to the complex model,some study lacks of validation by ground test datas. Comprehensive above problems, several reentry bodies are studied by numerical simulation method,which is verified by experimental data from wind tunnel, the complicated hypersonic flow phenomena around the reentry body models are reproduced. Several factors which affect the numerical simulation of the aerodynamic heating are analyzed, which provide the reference to realize the aerodynamic heating accurately simulation.The main works of this paper could be summarized as follows:(l)Numerical simulation method of the aerodynamic heating is selected after the comparison and analysis of the domestic and international research methods. Finite-volume numerical method and Roe scheme with LU-SGS implicit iteration are used to solve the3D compressible Navier-Stokes equations. The method is verified by simulating a typical model which has detailed experimental data from wind tunnel.(2)Definite conditions are ascertained to study the grid factors’influence on aerodynamic heating numerical simulation. Including grid construction methods, the circumferential direction grid distribution, flow direction grid distribution,normal direction grid distribution, the bottom grid scale, the bottom grid scale distribution, the orthogonality of grid,etc.(3)Heat flux distribution of the blunt cone is obtained at different angles of attack, the influence of grid construction methods at the nose is contrasted, the advantage of rectangular block is confirmed.The factor causes the mess of temperature field clouds at the nose is found and the solution is got by using a new type grid. The grid is optimized,results show that the normal direction grid distribution, the bottom grid scale have great influence on aeroheating numerical results,it must be small to a certain level to ensure adequate accuracy of heat flux precision.(4)Aerospace plane aerodynamic/aeroheating is sdudied by using numerical method, aerodynamic/aeroheating results are provided. Aerodynamic/aeroheating characteristics of Aerospace Plane are analysed. The computational grid is optimized where the simulation results are not coincide with the experimental data from wind tunnel, influence of the orthogonality of grid on aerodynamic heating numerical simulation are studied.(5)The simulation results are not coincide with the experimental data from wind tunnel on the rear of Aerospace Plane wing,where may have separation flow.Blunt fin/flat plate model with experimental data is selected to study the simulation of separation flow, results show that entropy fix has great influence on the separation flow aerodynamic heating numerical simulation.