Abstract
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.
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