Drag Reduction of a Near-Sonic Airplane by Using Computational Fluid Dynamics
Drag Reduction of a Near-Sonic Airplane by Using Computational Fluid Dynamics
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DOI：
10.2514/1.15059
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发表时间：
2005-09
期刊：
影响因子：
2.5
通讯作者：
Wataru Yamazaki;K. Matsushima;K. Nakahashi
中科院分区：
文献类型：
--
作者：
Wataru Yamazaki;K. Matsushima;K. Nakahashi
基于计算流体动力学方法，研究了近音速巡航飞机的气动外形优化问题。日本宇宙航空研究开发机构的比例实验超音速飞机模型，NEXST-1，被用作优化的基线模型。NEXST-1被接受为近音速飞机的候选者，因为在近音速状态下存在阻力桶。在本优化中，截面翼型形状和平面形状在马赫数0.98的近音速范围内彼此独立地进行优化。对于优化，遗传算法与非结构化网格欧拉模拟。优化结果表明，在近音速范围内，升阻比有了相当大的改善。翼型截面形状的优化和平面形状的优化分别降低了波阻和诱导阻力。
Aerodynamic shape optimization for an airplane cruising at a near-sonic regime is discussed based on computational fluid dynamics. Japan Aerospace Exploration Agency's scaled experimental supersonic airplane model, NEXST-1, was employed as the baseline model of the optimization. NEXST-1 was accepted as a candidate for a near-sonic airplane because of the existence of a drag bucket at a near-sonic regime. In the present optimization, the section airfoil shape and the planform shape were optimized independently of each other in the near-sonic regime of Mach number 0.98. For the optimization, a genetic algorithm was used with unstructured mesh Euler simulations. The results of the optimizations showed considerable improvement in the lift-to-drag ratio in the near-sonic regime. The optimization of the section airfoil shape and that of the planform shape yielded to the reduction of wave drag and induced drag, respectively.