Aerodynamic optimization design technology based on CFD becomes a very active object in the CFD field.
基于CFD的气动优化设计已成为当前计算流体力学研究的一个重要领域。
A four-stage high load LP turbine was optimized and redesigned by applying multistage aerodynamic optimization design process.
采用多级涡轮气动优化设计流程对某四级高负荷低压涡轮进行多级气动优化设计。
It is mainly important that the flow fields are simulated with a certain precision, as to aerodynamic optimization design in this method.
采用本文方法进行气动优化设计，流场计算要求有较高精度。
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。
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 optimization design of aerodynamic shape for reentry vehicles (ASRV) is a design problem of the complex engineering system, which often involves several subsystems and various parameters.
再入飞行器气动布局优化设计是一个复杂的工程系统设计问题，通常包含若干子系统和大量的设计参数。
The paper introduces aerodynamic configuration optimization design of lower Reynold number aeroplane using genetic algorithm, and makes prototypes to test feasibility and correctness of design.
试验结果表明该优化设计方法是十分有效的，可以用来对具有正常布局形式的飞机进行气动外形的优化设计。
The results of the numerical simulation will provide a more reliable basis for furthering the optimization of the aerodynamic design of gas solid two phase turbine blades.
数值模拟结果将为进一步优化气固两相透平叶片的气动设计提供更可靠的依据。
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。
A two-level aerodynamic optimization method based on surrogate models is proposed for aerodynamic optimization of high altitude long endurance UAV family configuration design.
针对高空长航时无人机族气动外形优化问题，通过借鉴多学科优化中的二级优化和代理模型方法。
In order to improve the efficiency and accuracy of the numerical calculation for the aerodynamic design of winglets, an optimization method based on multi-level response surfaces is proposed.
为了提高数值计算效率和准确性，提出了基于多级响应面法的确定翼梢小翼气动外形参数的一种优化方法。
A new method for optimization of aerodynamic design for centrifugal impellers is presented in the first part of this paper, and especially the essential thought of this method is described.
本文的第一部分介绍了一种离心叶轮气动优化的新方法，且特别侧重介绍其基本思想。
In the second design step, improvement of wing's aerodynamic characteristic is mainly depended on the weakening of shock which reduces wave drag during the wing section optimization.
在平面形状优化基础上，在机翼容积不变约束下，再采用剖面翼型优化设计，通过机翼剖面细微变化弱化较大马赫数下的激波、减小激波阻力。
In the second design step, improvement of wing's aerodynamic characteristic is mainly depended on the weakening of shock which reduces wave drag during the wing section optimization.
在平面形状优化基础上，在机翼容积不变约束下，再采用剖面翼型优化设计，通过机翼剖面细微变化弱化较大马赫数下的激波、减小激波阻力。
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