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双语推荐：翼型设计

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现代飞行器的精细化设计需求要求翼型参数化方法具有精准的翼型外形控制能力。依据标准的风洞模型公差要求，以五个典型翼型作为测试翼型，分别对Hicks-Henne参数化方法、样条参数化方法、PARSEC参数化方法和CST翼型参数化方法的翼型外形控制能力进行评估，依据每个翼型参数化方法的评估结果并结合其固有特点进行适应性分析。结果表明：四种翼型参数化方法对翼型外形的控制能力存在较大差别，具有不同的适用范围。评估典型翼型参数化方法的所得结果可指导设计人员依据具体的设计需求选择适当的翼型参数化方法。
Refinement design requirements of modern aircraft configuration require airfoil parametric methods to be of precise geometry control ability .Five representative classical airfoils are used as test airfoils and four clas-sical airfoil parametric methods’ geometry control ability is evaluated based on the standard wind tunnel model tolerance requirement .The four airfoil parametric methods are Hicks-Henne parameterization ,B-spline parame-terization ,PARSEC parameterization and CST parameterization respectively .Every parametric method’s appli-cability is analyzed based on the evaluation results and its inherent characteristics .T he evaluation results indicate that airfoil geometry control abilities are different between the parametric methods and each method has its own applicable scope .Geometry control ability evaluation of classical airfoil parametric methods can provide reference for designers to choose suitable airfoil parametric method for engineering problems .

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基于粒子群算法的研究基础,提出了基于粒子群算法的多模块协同的翼型优化设计方法。在高速风力机中被广泛应用的航空翼型在某些方面存在一定的不适应性。针对此问题,建立了基于多软件协同仿真且以翼型的升阻比为目标的自动化优化设计方法,并运用该方法对风力机中常用的NACA4412翼型进行优化设计。设计结果表明,用该方法优化后的翼型在气动性能方面有较大提高。
On the basis of the research on Particle Swarm Optimization(PSO),An airfoil optimization design method base on PSO with multi-objective is proposed in this paper.The avaiation airfoils,which was widely used in high speed wind turbine has some certain adaptability.According to this problem, Collaborative simulation is established based on software and aiming at airfoil lift-to-drag ratio of the automatic optimization design method,and using the method redesign a airfoil ,which is gen-erally used in wind turbine airfoil named NACA4412 .The results show that aerodynamic performance is improved greatly un-der this method with PSO.

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旋转机翼无人机由于兼具垂直起降和高速巡航性能而备受青睐,旋转机翼翼型不同于固定翼,对旋转机翼翼型的设计和气动特性的研究具有实际意义。针对旋转机翼翼型展开有弯度的前后对称翼型设计,通过亚音速多工况数值计算筛选出升阻特性最优的翼型——弯度10%、厚度12%的上凸下凹前后对称翼型GOE-10-12。为了验证数值计算的准确性,进行了3种低速工况(20 m/s、30m/s、40 m/s)的风洞试验,结果表明数值计算和试验获得的升力系数和阻力系数吻合较好,新设计的翼型具有良好的升阻力特性,适合应用于旋转机翼。
An unmanned aerial vehicle ( UAV) with rotational wings is popular because it can take off and land vertically and cruise at high speed. The airfoil with rotational wings is different from the airfoil with fixed wings. The difference is significant for the design of the airfoil with rotational wings and for the study of its aerodynamic charac-teristics. Therefore, we design a cambered ( upper surface convex and lower surface concave/USCLSC) and fore-and-aft symmetrical airfoils for the UAV with rotational wings. The subsonic numerical calculation is performed to determine the airfoil with the optimal lift drag ratio, whose maximum camber is 10%, and maximum thickness is 12%. To verify the accuracy of the numerical calculation, we conduct wind tunnel tests under three low speed work conditions:V=20 m/s, 30 m/s and 40 m/s. The test results, given in Figs.3 through 9, and their analysis show preliminarily that the lift coefficient and drag coefficient obtained with the numerical calculati

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船舶螺旋桨及舵均由水翼剖面组成,为了提高桨、舵的水动力性能,需要对水翼进行优化设计,以便得到水动力性能更好的桨及舵。提出一种基于线性权重处理的多目标优化算法,以降低阻升比和改善水翼表面压力分布为优化目标,将其应用到多目标水翼优化中。分别选取不同的攻角、不同翼型和不同的翼型表达函数进行优化设计。优化后得到的新翼型相对于原始翼型,具有低阻生比和较低的最小负压力系数,提高了翼型的升力效率和空泡性能。因此,验证了提出的多目标粒子群算法能够应用到多目标翼型优化设计的可行性。
Both ship propeller and rudder are composed of hydrofoil sections.In order to improve the hydrodynamic performance of propeller and rudder, the design of hydrofoil sections needs to be optimized to get the propeller and rudder with better hydrodynamic performance.The multi-objective particle swarm optimization algorithm based on linear-weight strategy was proposed for reducing the drag-lift ratio and improving the hydrofoil surface pressure dis-tribution.This algorithm was applied to the multi-objective hydrofoil optimization.Different attack angles, different hydrofoils and different hydrofoil expression functions were selected respectively for the optimization.The new hy-drofoil after optimization had lower drag-lift ratio and minimum negative pressure coefficient than the original one, which improved the lift efficiency and cavitation performance of the hydrofoil.Therefore, the feasibility of applying multi-objective particle swarm optimization to multi-objective hydrofoil

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基于（势流）涡方法开发了水平轴风力机叶片气动性能分析程序，采用自由尾迹模型对增加 O 型小翼和 L型小翼后的叶片气动设计性能进行分析，计算了风力机设计工况下的涡位置及诱导速度分布等气动性能参数，对比了增加小翼后功率输出情况。结果表明，增加小翼后风力机叶片在设计工况下功率系数有明显增加，下风向小翼功率提升高于上风向小翼。
A design and analysis procedure for rotor blades is developed based on vortex theo-ry.Based on free wake model,the aerodynamic performances of horizontal axis wind turbine ro-tor by adding spiroid O winglets and L winglet at the tip of the blade are studied numerically,the vortex location and induced velocity distribution in different conditions are investigated.The results show that the presence of winglet at the tip of the wind turbine blade improves the power coefficient at the design wind speeds,and downwind winglets are superior to upwind ones with respect to optimization of power.

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采用类别形状函数变换(CST)方法对翼型参数化描述;利用Fluent软件,进行翼型升力系数和阻力系数的气动计算;以升阻比最大为优化目标,通过拉丁超立方设计生成样本点,建立了径向基神经网络(RBF)代理模型;使用粒子群优化算法(PSO),在Isight平台上,实现对Clark Y翼型优化的整个过程。优化翼型升阻比比原始翼型提高了约10%,表明此种方法是可行的,可用于小型无人机设计的工程中。
The CST universal parametric geometry representation method was used to describe the parametric air? foil,and lift coefficient and drag coefficient of the designed airfoil was directly calculated by Fluent. The maxi? mum lift-drag ratio as the goal was achieved by employing PSO algorithm. The latin hypercube method was em? ployed to construct the initial sample points used in a RBF surrogate model. The software of Isight was used to realize the design processes. The maximum lift-drag ratio was significantly improved by about 10%. The result showed that this approach was feasible and could be used as reference for Mini-UAV design in engineering.

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为提高多段翼型增升效能,开展襟翼外形和缝道参数同时优化设计研究。优化算法采用遗传算法,以求解RANS方程为气动特性分析方法,通过椭圆方程控制生成多段翼型外形,同时优化缝宽、搭接量、襟翼偏角等位置参数和襟翼外形控制参数,实现多段翼型优化设计。设计实践表明,与只优化位置参数相比,同时优化襟翼外形和位置参数得到的多段翼型有更大的升力系数,方法是可行的,具有一定的工程应用前景。
The purpose is to enhance the aerodynamic performance of multi-element airfoil by searching for optimal shape and setting parameters .The procedure is driven by a genetic algorithm coupled with a RANS equations solver .Elliptic equations are used to automatically generate the multi-element airfoil shape,some design variables such as gap ,overlap,flap deflection and control parameters of flap shape are optimized to get excellent aerodynamic characteristic .Compared with the result that position parameters are only optimized ,multi-element airfoil optimized by the present method has higher lift coefficient .

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垂直轴风力发电机(简称垂直轴风力机)无需偏航装置,结构简单,维护方便,成本低,发展前景广阔。介绍了垂直轴风力机的种类,阐述了垂直轴风力机翼型的设计方法、气动性能、翼型分析和设计常用软件以及国内外翼型研究现状,总结了垂直轴风力机叶片翼型研究中存在的问题,并提出相应的对策,对垂直轴风力机的发展给出了一些建议。
Vertical Axis Wind Turbine(VAWT) has the advantages of easy maintenance ,low cost,without yaw device and broad prospect .Introduces the type ,wind airfoil design method ,the pneumatic performance and commonly used softwares of vertical axis wind turbine ,as well as domestic and foreign airfoil research status .Also summarizes the problems existing in the research of the vertical axis wind turbine airfoil profile ,and puts forward some corresponding measures .Finally,some suggestions on vertical axis wind turbine development have been presented .

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根据可折叠翼板展开机构的工作特性,提出增力型展开机构的设计方案,通过描述机构的运动方程和翼板驱动力矩的表达式,对新展开机构的动力特性作出详细分析,为可折叠翼板展开机构的设计方法提出了新的思路。
According to the work characteristic of the folding-bomb wing expansion device, the design scheme of the increasing-force type expansion device is presented. By discussing the movement equation of the device and driving moment expression of bomb wing, the dynamical characteristic of the new-type expansion device is analyzed in detail. So that the new design idea of the folding-bomb wing expansion device is provided.

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目前,基于Kriging代理模型的优化方法在气动优化设计中得到了广泛的应用,然而却并未能应用于气动反设计中。本文将翼型气动反设计问题转化为优化问题,利用基于Kriging模型的优化方法进行了翼型的单目标、多目标反设计,验证了Kriging模型在翼型单目标、多目标反设计中的适应性,并研究了模型加点准则对设计结果的影响;此外,将本文方法与多项式响应面模型优化方法、基于Adjoint的优化方法进行了比较,结果表明,该方法明显优于基于多项式响应面的优化方法,且与Adjoint方法相比,设计效率相当且具有更好的通用性。最后将本文方法应用于接近工程实际的在已有翼型基础上修改压力分布进行反设计,验证了本文方法的可行性。
Up to date,the Kriging-based optimization methods are widely used in the aerodynamic opti-mization design,however,it hasn’t been successfully applied to the aerodynamic inverse design problems. In this research,the Kriging-based optimization method is applied to the single and multi-point airfoil inverse design,and its feasibility to inverse design problems is validated;besides,the choice of infill criteria is inves-tigated.Moreover,this method is compared to the polynomial response surface based method (P-RSM)and the Adjoint-based method,the results show that the Kriging-based method outperforms the P-RSM,and has comparable efficiency with Adjoint-based method but better flexibility and easier to use.Finally,the current method is applied to engineering inverse airfoil design problems and its feasibility is validated.

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