为研究Busemann双翼翼型在高超声速机翼上的应用，构建了一种基于Busemann双翼翼型的高超声速机翼，研究其在高超声速流动中的气动特性和温度对其前6阶模态固有频率的影响。针对高超声速流动的复杂性和高超声速机翼涉及学科的多样性，首先从理论上证明高超声速Busemann双翼能够提高升阻比，然后通过数值模拟研究了Busemann双翼在高超声速流动中的气动特性，及其增升减阻和减小翼尖涡的机理，并使用分层理论简化高超声速机翼所涉及学科之间的复杂耦合关系，研究了温度对高超声速Busemann双翼模态的影响。结果表明：在高超声速流动中，Busemann双翼能够显著提高升阻比并减小翼尖涡的强度，相对于菱形单翼，Busemann双翼的升力系数增加了28.95%，阻力系数增大了13.58%，升阻比提高了13.53%，升阻比提高较为明显；同时，在1 300℃时，相对于菱形单翼的一阶固有频率，Busemann双翼的一阶固有频率提高了99.8%，说明Busemann双翼具有更好的抗弯能力；相对于在20℃时的一阶固有频率，Busemann双翼在1 300℃时的一阶固有频率下降了34.2%，说明不能忽略高温对Busemann双翼结构性能的影响。
To study on the performance of the hypersonic wing of Busemann biplane airfoils, a hypersonic wing based on the Busemann biplane airfoil is constructed. The aerodynamic characteristics in the hypersonic flow and the influence of temperature on the natural frequencies of the first six modes are studied. Considering complexity of the hypersonic flow and the variety of the disciplines involved, the Busemann biplane is proved theoretically to be able to improve the lift-to-drag ratio, and then the aerodynamic characteristics of the Busemann biplane in the hypersonic flow and its mechanism of reducing drag, increasing lift, and reducing wing tip vortex are studied by numerical simulation. In addition, the hierarchical theory is used to simplify the complex coupling relationship between the disciplines of hypersonic wings, and the effect of temperature on the mode of the hypersonic Busemann biplane is studied. It is shown that the Busemann biplane can significantly improve the lift-to-drag ratio of wings and weaken the strength of the wing tip vortex:the lift coefficient of the Busemann biplane is increased by 28.95%, the drag coefficient is reduced by 13.58%, and the lift-to-drag ratio is increased obviously by 13.53% of that the diamond monoplane. At the same time, at 1 300℃, the first-order natural frequency of the Busemann biplane increases by 99.8% of that of the diamond wing, showing that Busemann biplane have better ability to resist bending. The first-order natural frequency of the Busemann biplane at 1 300℃ decreases by 34.2% of that at 20℃, indicating that the effect of high temperature on the structural performance of the Busemann biplane cannot be neglected.
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