Mathematical model for takeoff simulation of a wing in proximity to the ground

Aircraft flying close to the ground benefit from enhanced efficiency owing to decreased induced drag and increased lift. In this study, a mathematical model is developed to simulate the takeoff of a wing near the ground using an Iterative Boundary Element Method (IBEM) and the finite difference scheme. Two stand-alone sub-codes and a mother code, which enables communication between the sub-codes, are developed to solve for the self-excitation of the Wing-In-Ground (WIG) effect. The aerodynamic force exerted on the wing is calculated by the first sub-code using the IBEM, and the vertical displacement of the wing is calculated by the second sub-code using the finite difference scheme. The mother code commands the two sub-codes and can solve for the aerodynamics of the wing and operating height within seconds. The developed code system is used to solve for the force, velocity, and displacement of an NACA6409 wing at a 4° Angle of Attack (AoA) which has various numerical and experimental studies in the literature. The effects of thickness and AoA are then investigated and conclusions were drawn with respect to generated results. The proposed model provides a practical method for understanding the flight dynamics and it is specifically beneficial at the pre-design stages of a WIG effect craft.     

风力机叶片翼型气动特性数值模拟

针对NACA63-215翼型绕流流动建立了二维可压缩湍流模型,利用商业软件NU-MECA进行了相应的数值模拟计算.湍流粘度分别采用基于RANS的Spalart-Allmaras和Baldwin-Lomax两种湍流模型来处理,得出了雷诺数为3×106时,翼型NACA63-215的升力系数和阻力系数随来流攻角的变化关系及压力分布图,并与试验数据进行对比.研究结果表明:Spalart-All-maras湍流模型比Baldwin-Lomax湍流模型在预测翼型失速后气动性能方面更加有效,Spalart-Allmaras湍流模型在大攻角下较易收敛且计算出的翼型气动性能与试验值更接近.     

地效翼气动力特性的数值预报

本文采用CFD技术,对存在地面效应时二维机翼在粘性流场中的空气动力特性进行了研究.结果表明:与模型试验数据相比,基于RANS方程的CFD方法能够准确预报机翼的气动升力和力矩.同时,除相对飞高外,翼剖面的厚度和拱度对地效翼的气动力特性也有重要影响.进而,作者对应用CFD分析或辅助地效翼气动力风洞试验进行了探讨.认为采用固定地板模拟地面效应与采用活动地板的模型风洞试验结果之间有很大差别,而风洞的壁面效应相比较而言可以忽略.     

大型船用轴流风机流场数值仿真及其气动噪声源特性研究

基于Realizable k-e双方程湍流模型,利用CFD软件建立了某型船用轴流风机内部流场的仿真模型,分析了转速1460rpm时,不同工况下轴流风机出口压力和效率随流量的变化关系,深入研究了叶轮区域的气体流动的压力和速度的分布、形成过程及相互关系。分析发现,在叶片叶顶区域,由叶顶间隙涡形成的叶顶间隙噪声是该轴流风机的主要气动噪声源;湍流强度与声功率级具有较为一致的分布趋势,湍流强度是影响噪声分布的重要因素。研究结果对分析大型船用轴流风机气动噪声产生机理具有参考价值,并为降低其噪声提供依据。     

地效翼艇三维组合翼气动特性计算分析

地效翼布局和翼型选择在很大程度上决定地效翼艇的性能和效能,对地效翼艇的设计至关重要。文章根据地效翼布局和翼型的特点,采用基于升力面理论的镜像法计算三维组合地效翼和简单地效翼在地效区和超出地效区的纵向气动特性参数,分析布局型式和外形参数对地效翼气动特性的影响。得到的组合翼在地效区内外比简单地效翼具有更好的升阻特性的结果,表明组合翼布局适合于掠海高飞型地效翼艇,研究也为地效翼布局型式、外形参数选择以及吹风模型制作提供了依据。     

潜艇组合型艉舵结构特征参数对水动力性能的影响分析

利用计算流体动力学工具CFX,合理选用有限体积法和RNG-εE湍流模型对NACA67．1-015型襟翼敞水舵进行CFD模拟验证计算,通过与试验数据进行比较,证明计算方法的合理性,对潜艇组合型艉舵在不同展弦比λ、艉弦比t^-下的流场进行数值模拟计算,得到其升力系数、阻力系数、压力中心系数曲线和压力分布图,通过对水动力系数曲线和压力分布图的分析,得到舵特征参数对水动力性能的影响规律。     

近地、水面时的飞行器动态稳定特性数值模拟

基于非结构动态网格重构技术,采用SA模型以及VOF方法,分别对NACA0012二维翼型自由空间、近地效应以及近水面效应的非定常运动流场进行了数值计算分析,并根据建立的基于小幅度强迫振动的组合动导数辨识方法计算了各个攻角下动导数。计算结果分析表明动导数计算方法准确可靠;中小攻角下,地面与水面以管道效应影响流场,均损失了动态阻尼,柔性的水面损失更多,动导数绝对值更小;大攻角时,两者表现为阻塞效应,柔性水面下的动态阻尼增大,动导数绝对值也变大;相比地面效应,柔性的水面影响范围更广。     

基于CFD仿真计算的襟翼舵水动力研究

襟翼舵作为一种可靠的、高升力的舵在最近几年内引起了广大设计工作者的重视影响,同时也有不少成熟的研究成果。对襟翼舵的研究主要集中在展弦比,主副舵面积比,转角比等方面,这些因素对襟翼舵的整体影响规律也已得到不少专家的解释。本文主要研究襟翼舵主副舵间间隙大小以及尺度效应对其水动力性能的影响,以普通NACA0020翼型为基本剖面建立不同间隙大小的襟翼舵模型,采用RANS方法计算得到了不同缝隙大小以及不同缩尺比下的襟翼舵升力阻力以及压力分布,并对周围涡结构以及流场进行分析,发现升力系数随着缝隙增大而减小,阻力系数先减小再增大的规律。同时随着襟翼舵尺度的增大,升力系数会随之增大,阻力系数会随之减小。文中以计算模型和实验数据进行对比,两者误差在5%以内,证明了计算结果的可靠性。     

飞机环控系统蝶形阀气动噪声特性及影响因素

为研究飞机环控系统管路蝶形阀气动噪声特性及影响因素,采用CFD软件与专业声学分析软件进行联合仿真,对气体流经阀门时的流场进行瞬态分析,将所得流场数据导入专业声学软件LMS Virtual.Lab,生成气动噪声声源,并建立气动噪声模型。分析结果表明:气体流过蝶形阀后产生较强烈的涡流扰动,导致管路和阀门壁面产生脉动压力,从而辐射气动噪声;蝶形阀气动噪声声压级频谱较宽,无明显主频率;阀门开度和气体流速会显著影响气动噪声声压级,在系统设计中应避免阀门长时间在低开度下工作。     

Experimental ivnestigation on flow fields of viscous fluid around two-dimensional wings and comparison with computational results

To examine the flow field of a viscous fluid around the trailing edge of a wing with respect to the Kutta condition or the Joukowski hypothesis, an experimental investigation into the velocity fields around two-dimensional (2D) wings NACA0012 and NACA4412 was carried out using an X-type hot-wire anemometer in a wind tunnel and the method of colored milk injection in a circulating water channel. The results of these investigations revealed that the flow of a viscous fluid at the trailing edge of a 2D wing is tangential to the face on the pressure side, and that the flow is very slow or reversed on the suction side due to separation when the angle of attack is greater than 7.5°. By flow visualization, a Kármán vortex street was found in the wake of both wings (NACA0012 and NACA4412) when the angle of attack was 5°. These results show that the ordinary Kutta condition with respect to the direction of outflow at the trailing edge is not necessarily satisfied in a viscous fluid, but the Kutta condition with respect to the pressure at the trailing edge is satisfied as usual. Numerical results, which have been obtained as the solution of Reynolds-averaged Navier-Stokes equations, show good agreement with above-mentioned experimental results. Therefore, CFD (Computational Fluid Dynamics) simulation has proved to be very effective for studying steady viscous flow around the trailing edge of a 2D wing.     

失速点上湿压缩对于跨音速压气机转子性能的影响

In order to study the effects of wet compression on a transonic compressor,a full 3-D steady numerical simulation was carried out under varying conditions.Different injected water flow rates and droplet diameters were considered.The effect of wet compression on the shock,separated flow,pressure ratio,and efficiency was investigated.Additionally,the effect of wet compression on the tip clearance when the compressor runs in the near-stall and stall situations was emphasized.Analysis of the results shows that the range of stable operation is extended,and that the pressure ratio and inlet air flow rate are also increased at the near-stall point.In addition,it seems that there is an optimum size of the droplet diameter.     

二维扁卵形体近壁面水动力干扰实验

对长度-厚度比为7.0的二维扁卵形体近平壁面运动的水动力特性进行了研究.拖曳水池试验选择了六种不同的壁面间距,五个攻角状态,将卵形体模型安装在U形槽中,保证流场的二维特性.Reynolds数范围从5×105到2×106.根据无界流实验结果,在数据处理中消除测力天平的安装角误差.给出了水动力系数相对于间距、攻角的回归公式,并划分了三个典型的干扰区域:升力区、混合区、阻塞区.实验表明:即使对于钝尾物体,也存在类似机翼的升力效应,无界流中扁卵形体的升力线斜率小于二维平板机翼的相应值.当物体离壁面较远时,水动力系数随攻角线性变化,壁面影响随间距减小而增大;当物体离壁面很近时,出现排斥现象,水动力系数随攻角的变化呈非线性特征.与其它参数相比,在大部分试验状态下,运动速度对水动力系数的影响较小.     

动力气垫地效翼船——21世纪水上高速客运的方向

本文简要地介绍了三种地效翼船，即动力增升地效翼船、动力气垫地效翼船和空气动力地效应船，其中着重介绍了动力气扩建地效翼船的优缺点，并以上海－南通航线为例，论证了动力气垫地效翼船的经济效益，由于动力气垫地效翼船具有高速、经济、安全、耐波性好、优良的两栖性和可登陆性，且设备简单，造价较低和多航态可海上游弋等一系列优点，因此很有可能成为２１世纪全世界水上高速运载工具的方向。     

基于热弹性流体动压润滑的柴油机曲轴主轴承润滑特性分析

基于平均流量模型和Greenwood/Tripp微凸体接触理论,采用有限元法与多体动力学结合的方法,考虑柴油机曲轴主轴承轴颈和轴瓦表面粗糙度、曲轴和轴承座的变形及热效应等影响因素,建立某四缸四冲程柴油机曲轴实体模型和数学模型,分析了曲轴轴承间隙、供油压力和温度、油槽宽度等参数变化时的主轴承润滑特性,并对主轴承进行了优化.最终结果表明,四缸四冲程柴油机第二道和第四道主轴承润滑情况较差,通过增大油槽宽度、减小滑油压力、增大轴承间隙、增加粗糙度等手段可以保证柴油机主轴承最小油膜厚度增加,最大油膜压力减小,实现良好润滑。     

海洋污损对叶切面性能影响的数值研究

通常情况下螺旋桨桨叶表面是抛光金属,没有涂装防污涂层,这使得桨叶表面易受污损的附着和侵蚀,然而污损对叶切面性能的影响却很少受到关注和研究。文章通过CFD方法对这种影响进行定量研究,并对产生影响的物理机制进行深入分析。采用SST k-ω湍流模型以NACA 4424翼型作为叶切面进行数值模拟,在海洋污损生物群落中选取藤壶作为桨叶污损对象,并在几何层面上直接进行建模。计算结果表明,污损会使得叶切面表面边界层分离更早,分离区域增大,这将显著降低叶剖面的升阻比C_L/C_D,进而导致螺旋桨推进效率大幅度减小。尽管如此,当污损高度超过一定值后,污损高度的增加对C_L/C_D的影响便会变得很小。数值计算与文献中试验结果吻合得较好。     

粒子群算法在翼型剖面优化中的应用

为设计出具有良好升阻比性能的翼型剖面,采用智能优化领域新兴的粒子群优化算法(PSO)结合面元法对翼型进行优化设计。文中给出了PSO算法的数学模型及其在翼型优化设计中的主要计算过程,并以Naca66mod翼型为原型进行设计。获取了翼型优化过程中每一步处的翼型剖面形状、翼型表面压力系数分布以及翼型的升力系数、阻力系数和最大厚度比,结果分析表明经过优化后的翼型与原型相比,具有升力系数增加,阻力系数减小这一有利的特征改变。同时采用CFD方法对两种翼型进行数值模拟计算,获得同上的结论,进而验证了PSO方法在翼型优化设计中的可行性。     

非均匀表面上移动的冲翼艇的横摇-垂荡-纵摇运动建模（英文）

Ground-effect vehicles flying close to water or ground often employ ram wings which generate aerodynamic lift primarily on their lower surfaces. The subject of this paper is the 3-DOF modeling of roll, heave, and pitch motions of such a wing in the presence of surface waves and other ground non-uniformities. The potential-flow extreme-ground-effect theory is applied for calculating unsteady pressure distribution under the wing which defines instantaneous lift force and moments. Dynamic simulations of a selected ram wing configuration are carried out in the presence of surface waves of various headings and wavelengths,as well as for transient flights over a ground obstacle. The largest amplitudes of the vehicle motions are observed in beam waves when the periods of the encounter are long. Nonlinear effects are more pronounced for pitch angles than for roll and heave. The present method can be adapted for modeling of air-supported lifting surfaces on fast marine vehicles.     

Hydrodynamics study of a BCF mode bioinspired robotic-fish underwater vehicle using Lighthill’s slender body model

This paper investigates the hydrodynamic characteristics of the rectilinear motion of a robotic fish underwater vehicle. This 2-joint, 3-link multibody vehicle model is biologically inspired by a body caudal fin carangiform fish propulsion mechanism. Navier–Stokes equations are used to compute the unsteady flow fields generated due to the interaction between the vehicle and the surrounding incompressible and Newtonian fluid (water) environment. The NACA 0014 airfoil aerodynamic profile has been designed to boost the swimming efficiency by reducing drag as the vehicle undergoes an undulatory/oscillatory motion. Using the Lighthill slender body model, a traveling wave mathematical function is defined to undulate the robotic fish posterior (caudal) region while the motion tracking is carried out by dynamic meshing technique. The results obtained show that though the net lift force approaches to zero, the net thrust or negative drag coefficient maintains a finite value dependent on kinematic parameters like tail beat frequency (TBF) and amplitude span (AS) at a given propulsive wavelength and the forward velocity of the vehicle. The results reveal the effects of TBF and AS on the coefficient of drag friction and the thrust force. Drag coefficients obtained from the simulations are compared and validated with the experimental results. The hydrodynamic results are found to be similar to the kinematic study results and suggest that TBF and AS play the most effective roles in the bioinspired propulsion technique. Relation of these parameters with propelling thrust force and forward velocity is also in conjunction over a given range of TBF and AS values.     

Empirical relation between the typhoon surge deviation and the corresponding typhoon characteristics: a case study in Taiwan

The relation between typhoon surges and typhoon characteristics measured at Kenfang Tidal Station on the northeast coast of Taiwan was studied in this paper. Typhoon characteristics include the typhoon center atmospheric pressure, the typhoon near-center wind speed, the typhoon storm radius, the distance between the typhoon center and the tidal station, and the typhoon approach tracks. The results show that the typhoon surge deviation is strongly dependent on typhoon characteristics. An empirical typhoon surge formula is proposed in terms of the typhoon wind speed, the typhoon storm radius, and the distance between the typhoon center and the tidal station. The coefficients in the empirical formula were evaluated, based on the measured typhoon surge data at Kenfang Tidal Station. The storm surge deviations at Kenfang Station during Typhoons Doug (1994) and Herb (1996) estimated using the proposed empirical formula were compared with the measured data as well as with the results of a numerical study.     

燃气轮机高压涡轮叶顶间隙变化规律的有限元分析

高压涡轮叶顶间隙会直接影响到燃气轮机的功率、效率、油耗和寿命。利用有限元等软件,建立了叶片、轮盘和机匣外环的实物模型;通过热结构耦合分析,计算得到各自在温度场和离心力场作用下的径向位移,进而得到叶顶间隙变化规律,并进行了分析。计算结果表明:温度场变化是引起叶片和轮盘径向变形的主要因素;离心力对轮盘径向变形的作用比对叶片径向变形的作用要显著得多;热和离心力变化是间隙变化的两个主要因素;叶片、轮盘和机匣的热响应不一致以及离心力对转子的拉伸作用导致其径向膨胀变形不匹配,进而引起间隙变化;快速增减速度对间隙的影响最为明显。