Correlation Analysis Between Simulation Parameters and Numerical Accuracy in High Supersonic External Flow Field
The three modeling methods were designed,including 6 NACA0012 airfoils with 2 trailing edge shapes,and 18 computational domain flow fields were established by combining three far-field distances.A unified grid strategy is used to generate the same number of grids,numerical simulations were performed based on SST k-omega/Spalart Allmaras turbulence models and ROE/AUSM flux types.The error rates of pressure coefficient,lift coefficient,and drag coefficient were calculated based on wind tunnel test data,and the relation-ship between the key simulation parameters and numerical accuracy was analyzed.The numerical results indicate that an inappropriate de-sign method for the sharp trailing edge will result in the maximum decrease in numerical accuracy,reaching 57.13％ .The choice of two sharp trailing edge modeling methods,NACA4 and Definition Formula,depends on the source and quantity of data points used in the modeling.There is a positive correlation between the number of modeling data points and numerical accuracy provided by Airfoil tools and NACA4,and the numerical performance of the data points provided by the former is better than that of the latter.The recommended values for far-field distance,turbulence model,and flux type are 16L,Spalart Allmaras,and AUSM,respectively.Considering the numerical er-ror rate,the optimal parameter configuration for the high supersonic external flow field is based on the defined formula design of the sharp trailing edge airfoil+16L far-field distance+Spalart Allmaras turbulence model+AUSM flux type.
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