论文部分内容阅读
为了进一步探索三维超声速流道的设计方法,采用一种预设壁面压力分布计算壁面型线的思想,并结合双特征线方法提出一种全三维超声速流动压力反问题的求解方法。在三维超声速流场设计中,可直接根据来流条件和壁面压力分布求解壁面的三维坐标,通过空间步进的方式,使得解在一系列解平面上推进,从而使得所设计的型面与预设的壁面压力分布相容。通过Prandtl-Meyer膨胀波的理论解验证了该格式的设计精度。根据预设的压力分布,设计了圆形和椭圆形入口的三维超声速喷管,并将设计方法与数值模拟进行对比验证。验证结果表明:所设计的流场与CFD计算得到的等值线符合得较好,因此基于双特征线的压力反问题求解方法具备三维超声速气动设计的能力,并具有纯三维、高精度、壁面压力分布可控的优势,对未来高超声速气动设计应用将起到重要的支撑作用。
In order to further explore the design method of three-dimensional supersonic flow channel, a method of calculating the wall profile by using the preset wall pressure distribution is proposed. Combined with the double characteristic line method, a solution method for the inverse problem of the full three-dimensional supersonic flow pressure is proposed. In the three-dimensional supersonic flow field design, the three-dimensional coordinates of the wall can be solved directly according to the flow conditions and the pressure distribution of the wall surface. The method of spatial step makes the solution advance on a series of solution planes, Set the wall pressure distribution compatible. The design accuracy of this format is verified by the theoretical solution of Prandtl-Meyer expansion wave. According to the preset pressure distribution, a three-dimensional supersonic nozzle with circular and oval entrances was designed, and the design method was compared with the numerical simulation. The verification results show that the designed flow field is in good agreement with the contour calculated by CFD. Therefore, the method based on bifurcation line for solving the pressure inverse problem possesses the capability of three-dimensional supersonic aerodynamic design and has the advantages of pure three-dimensional, high-precision, The advantages of controllable pressure distribution will play an important supporting role in the future application of hypersonic aerodynamic design.