Numerical Study On Drag Reduction Of Reverse Jet On A Hypersonic Wedge And Its Shape Optimizations

The leading edge of a hypersonic vehicle suffers serious shock resistance and heating problems. How to reduce drag and heat flux is one of the most important issues in the aircraft design. In this thesis, a numerical study on a hypersonic wedge with a power law leading edge is carried out by solving the N S equation. The shape optimization of the leading edge for different power parameters and the drag reduction study for reverse jet on the wedge with an optimized leading edge are conducted.First, a power leading edge of wedge shape optimization is analyzed. Computing for the supersonic aircraft flow field of different power law shapes, and a series of power law parameters are calculated. Second, the effects of the drag reduction with cold jet are analyzed. The computations for the optimized shape both with and without jet are carried for respectively, analyzing the drag reduction and the distribution of the flux. The results show that drag is lower with jet than that without jet, and the heat flux of the leading edge is weaker. Third, the variations of the distance between the leading edge and the front shock wave as a function of the pressure of the jet are investigated.The results show that when the power law parameter is 0.8, the drag reduction reaches an optimal value. When the pressure ratio reaches a critical value, reaches a minimum. This study provides useful information for hypersonic aircraft design.