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提出了基准流场与唇口平面形状分步优化的高超声速内收缩进气道设计方法。基准流场以反射激波不均匀性最小和总压恢复最大进行多目标优化设计,使用结合Tayler-Maccoll方程的有旋特征线方法(MOC)进行流场计算,获得双拐点母线内收缩锥基准流场。进气道唇口形状以沿流线积分(Streamline Integral Method,SIM)获得的进气道无黏阻力最小为目标进行优化设计,获得类椭圆形唇口平面形状。针对优化设计结果进行数值模拟,与传统直母线基准流场相比,双拐点母线基准流场反射激波后流动不均匀性下降40%左右,总压损失减少35%左右,总体性能提升明显。类椭圆唇口进气道在设计点的单位质量流量无黏阻力相较于圆形唇口降低6%,具有良好的压缩特性和气动效率,能够减弱进气系统对飞行器气动性能的不利影响。研究结果表明该方法是一种高效且实用的高超声速内收缩进气道设计方法。
The design method of supersonic constricted intake port with stepwise optimization of reference flow field and lip plane shape was proposed. The multi-objective optimization design of the reference flow field with minimum reflection shock nonuniformity and maximum total pressure recovery is carried out. The flow field is calculated by using the spin-on-line method (MOC) combined with Tayler-Maccoll equation. Flow field. Inlet lip shape The shape was optimized with the goal of minimizing the non-stick resistance of the inlets along the Streamline Integral Method (SIM) to obtain an oval-shaped lip plane shape. In order to simulate the results of optimization design, the flow inhomogeneity decreases by about 40% and the total pressure loss decreases by 35% compared with that of the traditional straight bus. The overall performance is obviously improved. Compared with the circular lip, the non-viscous resistance per unit mass flow at the design point of the elliptical lip port intake port is reduced by 6%, and has good compression characteristics and aerodynamic efficiency, which can reduce the adverse effect of the intake system on the aerodynamic performance of the aircraft. The results show that the proposed method is an efficient and practical method of design of hypersonic constricted inlets.