根据密切锥方法提出定平面形状乘波体设计, 以改善乘波体性能缺陷为目的生成双后掠外形。构建风洞试验模型在高超声速风洞中开展试验, 模型分别为弯头双后掠(BEND)和尖头双后掠(CUSP)乘波体, 并以一个单后掠外形作为对比模型。综合风洞试验和数值分析手段, 研究了前缘钝化的影响, 分析对比了模型的升阻力特性、纵向稳定性等性能, 发现前缘钝化对乘波体的升阻比影响很大, 而高超声速状态的数值模拟结果与风洞试验差别较小, BEND、CUSP模型的升阻比误差分别为0.19%、-0.23%，均小于0.5%。风洞试验和数值模拟数据表明, 双后掠乘波体在设计状态保持了“乘波”特性, 而且纵向稳定性得到很大提升, 验证了双后掠乘波体设计方法和设计外形的有效性。
A design method of the planform-customized waverider is proposed using the osculating-cone method, so as to enable the design of a double swept waverider to remedy the deficiencies of the waverider. To valid the proposed method, two models of the double swept waverider with a cusp head and a bend head are fabricated for wind tunnel tests, and a model of the single swept waverider is also constructed as the configuration for comparison. A variety of experiments at design-Mach-number conditions are performed in the hypersonic wind tunnel, and the Computational Fluid Dynamics (CFD) simulations are also conducted. The effect of bluntness, aerodynamic forces and longitudinal stability are studied. The results of comparison indicate that the bluntness of leading-edge area influences the lift-to-drag (L/D) ratio significantly; the aerodynamic performances obtained from wind tunnel tests are very close to those of CFD simulations, marking a difference in L/D of less than 0.5% in the design state. The data from both experiments and simulations show that the double swept waverider can maintain the "wave-riding" performance in the hypersonic state and its longitudinal stability is improved dramatically compared with that of the single swept configuration, verifying the effectiveness of the proposed method and the design configuration.
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