Abstract
For the sonic boom prediction and its minimization, it is very important to investigate the pressure signatures in the near field. In this paper, the near flow fields of a supersonic airplane are numerically simulated by solving the Euler equations using a space marching scheme. A solution-adaptive-grid method is incorporated in the computational procedure, where the grid in each marching plane is rearranged by monitoring the computed flow fields. The results show that this scheme gives the good prediction of the pressure signatures in the near field, and that the solution-adaptive-grid method improves the sharpness of the computed shock waves and the accuracy of the pressure signatures in the near field.
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