Application Of Fluid/Solid Coupling Heat Transfer Numerical Simulation To Hypersonic Wind Tunnels

According to the aims and requirements of the wind tunnel tests for hypersonic vehicles, the total temperature of the gas is very high. Since many structures of wind tunnel is in the hypersonic flow, the aerodynamic heating is serious. When the high temperature gas in hypersonic wind tunnel passes the nozzle, the surface temperature of throat may be high beyond the limit of material without cooling. The area of throat may change because of the high temperature, and this will affect the quality of the flow-filed. In previous, the structure design of the hypersonic wind tunnel only takes engineering estimate. The modern hypersonic wind tunnel design demands a method with more precision method because of the cruelty aerodynamic heating.This thesis studies an integrated method that takes into account the solid-fluid interaction and this method is presented to the heat conduction of hypersonic wind tunnel. Numerical results of the two-dimensional and three-dimensional coupling show that the method in this paper is correct. The M12 nozzle of FD-17 and it's cooling system are calculated, and the results validate that the method is feasibility and correctness to calculate thermal response of hypersonic wind tunnel. Then, the integrated method is applied to simulate the thermal environment of the nozzle of FD-22 and the HB-2 standard model. The solution demonstrates the material of nozzle and the balance in HB-2 is under normal working environment during test.The research in this paper is assisted in designing the structure of nozzle in hypersonic wind tunnel. Simplifications are made to the structure of real nozzle because of the complexity, so the research and conclusions in this paper are preliminary, based on which later research can be carried out.This thesis contains five chapters.In the instruction, the research background is presented, and the development of integrated solid/fluid numerical simulation is reviewed. In the last, the main work of this paper is introduced.In chapter 2 the thesis of heat conduction and fluid dynamics are presented, and it also introduces the characteristics of flow-field and thermal response on supersonic aircraft.Chapter 3 is the main part of the paper. In this part the way of carrying out the CFD and the NHT is introduced. The factors which effect on heat conduction are analyzed particularly. Based on the energy integration relation within the wall cell, a type of integrated solid/fluid numerical method is introduced. Benchmark solutions are calculated and compared with available solutions to validate check code consistency and accuracy. The comparisons show good agreement.Chapter 4 is devoted to the application of the integrated method presented in this thesis to the flow-field and thermal response on hypersonic wind tunnel. By using the integrated method a nozzle and its cooling system are calculated. The thermal environment of a standard model and the balance in it is calculated.The last part is the concluding remarks of the thesis.