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充分考虑伴随方法的梯度求解的准确性、CFD计算量小等显著优点,研究了引入基于伴随方法的梯度信息的响应面模型构造问题,发展了基于梯度信息改进的响应面方法,提高了多设计变量适应性及优化效率;针对悬停/前飞/机动状态下的旋翼翼型升阻比、阻力发散马赫数、最大升力等气动特性精确分析需求,分别提出了对应的合理气动计算策略;为有效适应旋翼翼型复杂气动设计问题,发展了基于伴随方法与响应面法有效结合、针对悬停/前飞/机动状态对应气动计算策略的一种较实用高效的旋翼翼型气动优化设计策略,提高了计算精度、鲁棒性与优化效率,进行了典型OA309旋翼翼型算例验证,优化后旋翼翼型与原OA309翼型相比,综合性能有较好改善,研究表明,所发展的气动设计策略是有效、可行的。
Considering the accuracy of the concomitant method and the small amount of CFD, the response surface model based on the gradient information of the adjoint method is studied. The response surface method based on the gradient information is developed and the multi-design Variable adaptability and optimization efficiency. According to the precise analysis of aerodynamic characteristics such as lift-drag ratio, resistance-diverging Mach number and maximum lift in rotor / forward / maneuver states, corresponding reasonable aerodynamic calculation strategies are proposed respectively. For In order to effectively adapt to the complex aerodynamic design of rotor airfoils, a more practical and efficient aerodynamic optimization design scheme of rotor airfoils is developed based on the effective combination of incidental method and response surface method, aiming at the aerodynamic calculation strategy of hovering / forward / maneuvering state, The computational accuracy, robustness and optimization efficiency are improved. A typical example of OA309 rotor airfoil is validated. After optimization, the rotor airfoil has a better overall performance compared with the original OA309 airfoil. The results show that the developed aerodynamic Design strategy is effective and feasible.