Calculation Of Aerodynamic Heating And Transient Surface Temperature For Hypersonic Aircraft

Aerodynamic heating is one of the most critical problems for high-speed or hypersonic vehicle design. It's very difficult to solve some problems with numerical methods, which employ N-S equation to predict aerodynamic heating. Because the numerical results are greatly influenced by turbulent flow model, mesh scale nearby wall, numerical format and so on. Besides, it requires large computer running time and storage. The cost of a flight test or a ground experiment is always high and the testing cycle is typically long. Consequently, it is necessary to develop efficient engineering methods for calculating aerodynamic heating.The project"Software Development of Aerodynamic Heating and Transient Surface Temperature Calculation for Hypersonic Aircraft", supported by the Chengdu Aircraft Design and Research Institute, is aimed to develop software for calculating aerodynamic heating and transient surface temperature of Hypersonic Aircraft. The software could be adopted to predict aerodynamic heating and temperature of the thermal protection system in an engineering design. The main works of this paper could be summarized as follows:(1) Firstly, the methods used to calculate aerodynamic heating were analyzed and summarized. Surface pressure distribution of high-speed or hypersonic vehicle is attained by some engineering methods, such as Newton method, tangent-wedge/cone method, and Prandtl-Meyer expansion wave and so on. Parameters at the edge of the boundary layer are calculated by using constant entropy conditions and perfect gas equations for ideal gas or characteristic equation of high temperature transport gas for equilibrium gas.(2) Based on the reference enthalpy method, the heat flux and transient surface temperature of laminar flow, turbulent flow at stagnation point and other places were predicted respectively by the classical heat flux formula. Equivalent cone method is adopted to predict heat flux with an angle of attack. Taking a blunted cone for example, the simulated results indicate that the engineering method consumes less time and is workable.(3) Due to the intensive bow shock, it's necessary to discuss variable entropy contribution for the nose of hypersonic vehicle. Shock shape and mass conservation method and the total pressure method are developed to calculate heat flux in this paper.(4) Software of Aerodynamic Heating and Transient Surface Temperature Calculation for Hypersonic Aircraft is developed.The method introduced in this paper could be used to calculated the aerodynamic heating and transient surface temperature efficiently,especially for complete time histories flight. These methods require less time and lower cost. As a result, application of the software in hypersonic aircraft design will be predicted.