A new penalty function method is used for the constrained aerodynamic optimization.
提出了一种快速应用型罚函数法来求解有约束气动优化问题。
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。
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。
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。
But the aerodynamic optimization of the turbomachinery blade, especially the transonic compressor blade, is still a challenge area.
但是叶轮机械，尤其是跨音速轴流压气机叶片的气动优化设计仍然是一个具有挑战性的研究领域。
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。
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。
Finally, zero order variable-fidelity aerodynamic optimization management framework and search algorithm were demonstrated on an airfoil optimization of UAV with a flying wing.
最后，设计了零阶变可信度气动特性优化管理结构与搜索算法，对某飞翼型无人机的翼型进行了气动优化。
An aerodynamic optimization method is described which is based on dynamic boundary control. This method is according to the idea of controlling the boundary of transforming object.
本文根据控制变形物体边界变化的思想，建立了一种基于动态边界控制的气动优化设计方法。
After aerodynamic optimization of an unmanned vehicle with the methods mentioned above, the lift coefficient has an increase of 21 % and the ratio of lift to drag has an increase of 6. 7%.
通过优化无人机外形取得了有意义的结果，优化后升力系数增加了21%，升阻比提高了6.7%。
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。
For aerodynamic shape optimization, the approximation management framework (AMF) method was used to organize and manage the variable-fidelity models.
在气动外形优化中，采用近似模型管理结构(amf)方法，对变可信度模型进行组织和管理。
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。
The aerodynamic efficiency is compared with bi objective optimization airfoil's, to identify the advantage of adaptive airfoil.
为验证自适应翼型增益的效果，计算了双目标优化翼型的气动特性。
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。
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。
Numerical results of symmetric arc airfoil and NACA65A006 airfoil show that aerodynamic efficiency of adaptive airfoil is better than that of bi objective optimization airfoil.
本文计算了对称圆弧翼型和NACA 6 5 A0 0 6翼型。 计算结果表明，自适应翼型比双目标优化的翼型有更好的气动特性。
To increase the efficiency of the multidisciplinary optimization of aircraft, an aerodynamic approximation model is improved.
在比值修正模型所构造的气动近似模型的基础上，引入了基于实例的推理技术对其加以改进。
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。
An optimization method is used to obtain deflection Angle of control surface and the aerodynamic efficiency of airfoil is calculated.
用数值优化方法取得自适应翼型最优的舵面偏角，并计算其气动特性。
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。
This article presents a two-step optimization based on a surrogate model for the aerodynamic shape optimization in a viscous flow.
提出了基于代理模型的两步优化方法，用于翼型在黏性流场中气动外形的优化设计。
This article presents a two-step optimization based on a surrogate model for the aerodynamic shape optimization in a viscous flow.
提出了基于代理模型的两步优化方法，用于翼型在黏性流场中气动外形的优化设计。
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