蓝庆生, 赵玉新, 赵一龙, 刘红阳. 三维超声速流动的压力反问题[J]. 空气动力学学报, 2017, 35(3): 429-435. DOI: 10.7638/kqdlxxb-2016.0156
引用本文: 蓝庆生, 赵玉新, 赵一龙, 刘红阳. 三维超声速流动的压力反问题[J]. 空气动力学学报, 2017, 35(3): 429-435. DOI: 10.7638/kqdlxxb-2016.0156
LAN Qingsheng, ZHAO Yuxin, ZHAO Yilong, LIU Hongyang. Pressure inverse problem of three-dimensional supersonic flow[J]. ACTA AERODYNAMICA SINICA, 2017, 35(3): 429-435. DOI: 10.7638/kqdlxxb-2016.0156
Citation: LAN Qingsheng, ZHAO Yuxin, ZHAO Yilong, LIU Hongyang. Pressure inverse problem of three-dimensional supersonic flow[J]. ACTA AERODYNAMICA SINICA, 2017, 35(3): 429-435. DOI: 10.7638/kqdlxxb-2016.0156

三维超声速流动的压力反问题

Pressure inverse problem of three-dimensional supersonic flow

  • 摘要: 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。

     

    Abstract: In order to explore valid methods for three-dimensional supersonic flow design, a technology was proposed to solve the pressure inverse problem by finding inviscid contour on the basis of a preassigned pressure distribution along the wall. A bicharacteristic algorithm is used to solve the inverse problem. Three-dimensional wall coordinates can be calculated directly according to the flow condition and predetermined boundary pressure. The designed three-dimensional contour can be compatible with preassigned pressure distribution by moving forward the solution plane along the x coordinate. The accuracy order of the solver was tested by comparing numerical solutions with analytical results of Prandtl-Meyer expansion wave. Three-dimensional supersonic nozzles with round or oval inlet were designed in this paper on the basis of one-dimensional pressure distributions. The reliability of the solver was validated by corresponding CFD numerical simulations. It can be found that the numerical solutions of the present solver are in good agreement with those of CFD simulations. The solver has the ability for three-dimensional supersonic aerodynamic design by solving the inverse problem based on the bicharacteristics method. Moreover, this solver has advantages of high accuracy, pure three-dimensional solutions, and controllable wall pressure distribution. The method has promising potential of playing a supporting role in the applications of further hypersonic aerodynamic design.

     

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