The Calculation Method Of Aerodynamic Heating With United Numerical And Engineering Algorithm

Heat barrier imposed by aerodynamic heating is one of the mostcritical problem for very high speed flying vehicles,especially for reentryvehicles.Strict performances of aerodynamic and requirements of thermalprotection are put forward.This thesis is aimed at developing TheCalculation Method of Aerodynamic Heating with United Numerical andEngineering Algorithm.Main works of this thesis could be summarized as follows:Firstly,an overview of the development of hypersonic aircrafts and theaerodynamic heating calculating methods developed by the scholars. Alsodiscrete schemes suitable for hypersonic numerical simulation aresummarized, including FVS ,Roe's FDS ,the latest AUSM + up, TVD,ENO, WENO, etc.Secondly, a 2-d numerical simulation code to solve full N-S equationwith finite volume and unstructured grids has been presented.The code canprocess the triangle, quadrilateral mixed grid. For nonviscous fluxdiscrete ,the latest AUSM+up scheme is used. With MUSCL methodreconstruction method, higher order accuracy is achieved.Least squaremethod is used to calculate gradient.The code employs third-order andfourth-order Runge-Kutta methods. Now, the code provides symmetricalboundary conditions, wall boundary conditions and far field boundaryconditions.With NASA Langley research center's experience, the domesticexisting research foundation and the available applications,the calculationmethod of aerodynamic heating with united numerical and engineeringalgorithm has been put forward.Also related code has been developed.Thismethod modifies engineering calculation data by numerical calculationdata, thus the overall efficiency and accuracy is improved.