This paper develops a hypersonic aerothermal simulation method for missile slot flow. The finite volume method of structure grid solver is developed for solving Euler and Navier-Stokes equations. The solver includes P...This paper develops a hypersonic aerothermal simulation method for missile slot flow. The finite volume method of structure grid solver is developed for solving Euler and Navier-Stokes equations. The solver includes Park＇s two temperature model and the air multi-species reaction model. The second-order accuracy TVD numerical method was deduced to compute the hypersonic aeroheating which improves the computational efficiency. Computational results are given to show the high accuracy comparing to the existing experimental data.展开更多
A rapid approach to hypersonic aeroheating predictions in the stagnation region and downstream is developed in the present paper.The engineering method is used to calculate inviscid hypersonic flowfields to reduce tim...A rapid approach to hypersonic aeroheating predictions in the stagnation region and downstream is developed in the present paper.The engineering method is used to calculate inviscid hypersonic flowfields to reduce time cost,and a combination of the mass flow balance technique and the axisymmetric analog is proposed to account for the entropy swallowing effects.A three-dimensional linear method is derived to fit the vehicle surface flowfields.Then a new axisymmetric analog method based on linear flowfields and linear surface equations is developed,with the complexity and computational cost reduced dramatically.In the stagnation region,an implicit surface fitting is introduced to approximate the primary curvatures and a robust aeroheating prediction method is constructed.The proposed approach is verified on a variety of configurations including spherically blunted cone,double ellipsoid and aerospace vehicle.Numerical results indicate the followings:1)The approach predicts aeroheating in about one second and the results agree well with CFD simulations and wind-tunnel measurements;2)with the help of entropy correction,the precision is further improved in the streamline diverging regions on the vehicle surface,while little improvement is found after entropy correction in the regions where the streamlines do not diverge.展开更多
Aeroheating prediction is a challenging and critical problem for the design and optimization of hypersonic vehicles.One challenge is that the solution of the Navier-Stokes equations strongly depends on the computation...Aeroheating prediction is a challenging and critical problem for the design and optimization of hypersonic vehicles.One challenge is that the solution of the Navier-Stokes equations strongly depends on the computational mesh.In this letter,the effect of mesh resolution on heat flux prediction is studied.It is found that mesh-independent solutions can be obtained using fine mesh,whose accuracy is confirmed by results from kinetic particle simulation.It is analyzed that mesh-induced numerical error comes mainly from the flux calculation in the boundary layer whereas the temperature gradient on the surface can be evaluated using a wall function.Numerical schemes having strong capability of boundary layer capture are therefore recommended for hypersonic heating prediction.展开更多
基金supported by the National Natural Science Foundation of China(10872050)the Fundamental Research Funds for the Centred Universities (DUT11ZD(G)01)
文摘This paper develops a hypersonic aerothermal simulation method for missile slot flow. The finite volume method of structure grid solver is developed for solving Euler and Navier-Stokes equations. The solver includes Park＇s two temperature model and the air multi-species reaction model. The second-order accuracy TVD numerical method was deduced to compute the hypersonic aeroheating which improves the computational efficiency. Computational results are given to show the high accuracy comparing to the existing experimental data.
基金supported by the Doctorate Creation Foundation of Northwestern Polytechnical University (Grant No. CX200902)
文摘A rapid approach to hypersonic aeroheating predictions in the stagnation region and downstream is developed in the present paper.The engineering method is used to calculate inviscid hypersonic flowfields to reduce time cost,and a combination of the mass flow balance technique and the axisymmetric analog is proposed to account for the entropy swallowing effects.A three-dimensional linear method is derived to fit the vehicle surface flowfields.Then a new axisymmetric analog method based on linear flowfields and linear surface equations is developed,with the complexity and computational cost reduced dramatically.In the stagnation region,an implicit surface fitting is introduced to approximate the primary curvatures and a robust aeroheating prediction method is constructed.The proposed approach is verified on a variety of configurations including spherically blunted cone,double ellipsoid and aerospace vehicle.Numerical results indicate the followings:1)The approach predicts aeroheating in about one second and the results agree well with CFD simulations and wind-tunnel measurements;2)with the help of entropy correction,the precision is further improved in the streamline diverging regions on the vehicle surface,while little improvement is found after entropy correction in the regions where the streamlines do not diverge.
基金supported by the National Natural Science Foundation of China(50836007,90816012,10621202.)
文摘Aeroheating prediction is a challenging and critical problem for the design and optimization of hypersonic vehicles.One challenge is that the solution of the Navier-Stokes equations strongly depends on the computational mesh.In this letter,the effect of mesh resolution on heat flux prediction is studied.It is found that mesh-independent solutions can be obtained using fine mesh,whose accuracy is confirmed by results from kinetic particle simulation.It is analyzed that mesh-induced numerical error comes mainly from the flux calculation in the boundary layer whereas the temperature gradient on the surface can be evaluated using a wall function.Numerical schemes having strong capability of boundary layer capture are therefore recommended for hypersonic heating prediction.
