In this dissertation, Numerical Aerodynamic Optimization method is attempted to apply in the inlet design.
本文尝试采用气动优化设计方法进行进气道的设计。
The method consists of two parts: aerodynamic performance calculation based finite blade vortex theory and aerodynamic optimization design based genetic algorithms.
该方法分为两部分：基于有限片桨叶涡流理论的气动性能计算和采用遗传优化算法的优化设计。
The aerodynamic figuration of the normal MAV configuration was optimized applying the method of the combinative of single and multidisciplinary design optimization.
采用单学科优化和多学科优化相结合的方法对常规气动布局进行了气动外形优化，并比较分析了单、多学科的优化结果，得出重要结论。
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