Experimental investigation of counter-rotating four vortex aircraft wake

An experimental investigation on the wake vortex formation and evolution of a four vortex system of a generic model in the near field and extended near field as well as the behaviour and decay in the far field region has been conducted by means of hot-wire anemometry in a wind tunnel. The results were obtained during an experimental campaign as part of the EC project “FAR-Wake”. The model used consists of a wing–tail plane configuration with the wing producing positive lift and the tail plane negative lift. The circulation ratio of tail plane to wing is ?0.3 and the span ratio is 0.3. Thus, a four vortex system with counter-rotating neighboured vortices exists. The model set-up was chosen on the condition to create a most promising four vortex system with respect to accelerate wake vortex decay by optimal perturbations enhancing inherent instability mechanisms. The flow field has been investigated for a half plane of the entire wake up to a distance of 48 span dimensions downstream of the model. The results obtained at 1, 12, 24 and 48 span distances are shown as non-dimensional axial vorticity and vertical turbulence intensities. A significant decay in peak vorticity, swirl velocity and circulation is observable during the downward motion of the vortices. Spectral analysis of the unsteady velocity data reveals a peak in the power spectral density distributions indicating the presence of a dominating instability. Using two hot-wire probes cross spectral density distributions have also been evaluated, which highlight the co-operative instability leading to a rapid wake vortex decay within 30 span dimensions downstream.     

喷流对飞机尾流涡影响的试验研究

飞机产生的尾流涡,特别是大尺度的翼尖涡,对尾随其后的飞行器是非常有害的,本文旨在探索利用飞机发动机产生的喷流加速尾流涡消亡的方法。试验采用简化的飞机模型(有尾翼),建立了包含一对翼尖涡及一对反向旋转的尾翼涡(通过以负迎角安装尾翼得到)的4涡尾流系统。在无外来扰动的情况下,不同的尾翼设置下得到的尾翼涡对翼尖涡的作用效果不同,有的能导致翼尖涡提前消亡,有的则不能。考察了不同强度的喷流对不同4涡尾流系统的影响,且作为对比,对无尾翼(2涡系统)及无喷流下的各种情况也分别作了观测。试验在拖曳水槽中进行,运用体视粒子图像测速(SPIV)技术,观测了与模型拖曳方向垂直的、从机翼后缘到下游约45翼展间均布的一系列切面。结果表明:当喷流直接作用于涡时,其效果主要取决于两者之间的初始距离及相对强度;而当喷流作用于整个4涡尾流系统时,其引入的扰动对不同的系统均能起到一定程度的改善作用,这种作用的关键在于利用喷流优化对翼尖涡进行扰动的机制,而不仅仅取决于喷流的强度。     

基于TOPSIS方法的海上预警机防空作战效能评估

针对目前预警机作战效能评估方法中的几点不足,提出用TOPSIS方法来评估海上预警机防空作战效能。根据预警机系统作战效能的多层次性,采用层次分析（AHP）法建立了海上预警机防空作战效能三层评估模型,并通过应用示例对3种海上预警机的防空作战效能进行分析,得到了理想评判效果。     

翼梢装置对机翼颤振特性影响研究

机翼加装翼梢装置在气动上可以起到减小飞机的诱导阻力、提高升阻比、耗散强翼梢涡等作用,但是它也使飞机的结构特性发生了变化,尤其是颤振特性。采用MSCPatran,MSCFlds建立基本翼及几种带翼梢装置机翼的动力学有限元模型和非定常空气动力网格,应用MSCNastran求解序列SOL103对其进行固有模态分析,利用求解序列SOL145进行颤振分析,通过对比分析得到翼梢装置对机翼的振动和颤振特性影响,为飞机翼梢装置设计提供依据。     

Influence of different flap settings on the wake-vortex structure of a rectangular wing with flaps and means of alleviation with wing fins

This paper presents the results of an experimental investigation of the wake-vortex structure behind a flapped rectangular wing. The wind-tunnel test is part of a project funded by the German Research Association (DFG) to investigate the flow structure in the wake of wings with different flap extensions. The purpose of this investigation is to study the main features of lift generated vortices in order to find ways to alleviate hazardous wake vortex encounters for following airplanes during start and approach such that an increase in airport capacity can be achieved. First, the wake structure at different flap settings is investigated by measuring the velocity field at different positions in the near field behind the wing. The measured data are evaluated in terms of vortex parameters such as core radius, maximum tangential velocities, circulation distributions, turbulence levels and maximum induced rolling moments on a following aircraft. Then additionally, for one flap setting, means of alleviation are examined with a wing fin mounted at different positions on the wing. Alleviation is judged by the decrease of the maximum induced rolling moment. A significant reduction is achieved for a wing fin placed near the outboard edge of the flap.     

A new vortex sheet model for simulating aircraft wake vortex evolution

A new vortex sheet model was proposed for simulating aircraft wake vortex evolution.Rather than beginning with a pair of counter-rotating cylindrical vortices as in the traditional models,a lift-drag method is used to initialize a vortex sheet so that the roll-up phase is taken into account.The results of this model report a better approximation to a real situation when compared to the measurement data.The roll-up induced structures are proved to influence the far-field decay.On one hand,they lead to an early decay in the diffusion phase.On the other hand,the growth of linear instability such as elliptical instability is suppressed,resulting in a slower decay in the rapid decay phase.This work provides a simple and practicable model for simulating wake vortex evolu tion,which combines the roll-up process and the far-field phase in simulation.It is also proved that the roll-up phase should not be ignored when simulating the far-field evolution of an aircraft wake vortex pair,which indicates the necessity of this new model.     

The turbulent decay of trailing vortex pairs in stably stratified environments

The decay of trailing vortex pairs in thermally stably stratified environments is investigated by means of large eddy simulations. Results of in-situ measurements in the wakes of different aircraft are used to find appropriate intitializations for the simulation of wake turbulence in the quiescent atmosphere. Furthermore, cases with weak atmospheric turbulence are investigated. It is shown that the early development of the vortices is not affected by turbulence and develops almost identically as in 2D simulations of wake vortices in stably stratified environments. In a quiescent atmosphere the subsequent vortex decay is controlled by the interaction of short-wave disturbances, owing to the aircraft induced turbulence, and baroclinic vorticity, owing to stable stratification. As a consequence, vertical vorticity streaks between the vortices are induced which are substantially intensified by vortex stretching and finally lead to rapid turbulent wake-vortex decay. When in addition atmospheric turbulence is also present, the long-wave instability is dominantly promoted. For very strong stratification (Fr<1) it is observed that wake vortices may rebound but lose most of their strength before reaching the flight level. Finally, the simulation results are compared to the predictive capabilities of Greene's approximate model.     

翼尖涡流场特性及其控制

大型运输飞机的尾涡系是诱发后继小型飞机空难的重要原因,需要有效的涡控制装置来削弱其强度.通过风洞实验,研究了翼型为NACA23016的矩形半机翼模型翼尖尾涡流动结构和控制方法.应用七孔探针空间流场定量测试技术研究了翼尖涡的流动结构,给出了翼尖尾涡在下游两倍弦长距离内的速度和压力场分布随迎角变化的规律.在机翼翼梢布置不同组合方式的翼梢涡扩散器,来控制翼尖涡.研究结果表明,正负90°和60°安装角的双翼梢涡扩散器可将翼尖涡涡核的静压增加60%以上.其旋涡强度削弱机理为:翼梢涡扩散器将集中的翼尖涡破碎分成两个或多个强度更弱的旋涡.在流体粘性的作用下,旋涡能量耗散更快,可有效地削弱翼尖尾涡的强度.     

飞机尾流的快速建模方法

尾流的强度主要由飞机的飞机重量、飞行速度和机翼形状所决定和仿真尾流的保守被动模型可很好的描述尾流系统中水蒸汽、位温等保守被动量的运动演化规律,但这种参数仿真时间长、对计算机要求高,不能实时预测任一机型所产生的尾流的状态分布特性.为此提出了一种尾流的快速建模方法,很好的解决了以往尾流实时仿真时的缺点,为飞机飞行过程中实时预测前机尾流的影响区域提供理论依据,从而减少尾流事故的发生.      

新概念机翼尾流特性实验

大型飞机常采用开启襟翼以增大机翼升力系数,实现较大迎角的起飞和降落,而机翼在大迎角状态下,翼尖会产生能量集中且自由消散时间长的飞机尾涡,严重影响后续起降飞机的安全。基于Rayleigh-Ludwieg不稳定性,提出一种新概念飞机襟翼布局,通过水槽实验发现:新概念布局的襟翼对翼尖涡的消散具有明显的促进作用,不同参数组合下襟翼涡对翼尖涡的运动特性和能量变化的影响均有不同。实验结果也为飞机尾流控制的研究提供了参考,在满足飞行力学设计的基础上,合理运用增升装置构建四涡系统可以有效促进飞机尾流的消散,提高机场飞机起降效率。     

四涡系统构建及其特性的实验研究

飞机尾涡是与升力相关的固有流动现象,威胁着机场附近的飞行安全,同时也限制了机场使用效率。在矩形机翼翼尖以一定方式安装涡流发生器,产生与主涡旋向相反的小涡,来构建一种具有自我消散机制的四涡系统,能实现尾涡集中能力的快速消散。结合流动显示和粒子成像测速(PIV)测量,探索了在不同的参数匹配下,下游25个翼展范围内该四涡系统的空间发展过程、涡量发展曲线,以及45个翼展范围内主涡环量的衰减程度。实验结果表明,受小涡诱导,尾涡出现了相交不稳定性,主涡提前破裂,涡量随之降低。当小涡和主涡的初始环量比为-0.581、初始距离比为0.5时,45个翼展范围内,主涡环量衰减34.7%。该实验结果为低尾流机翼的设计提供了一定的参考。     

变体翼梢小翼的减阻机理数值模拟

总结了对翼梢小翼减阻效果影响最大的几何参数,在此基础上采用数值模拟方法研究了这些几何参数的最佳变化范围,为变体翼梢小翼设计提供理论依据.并从气动性能、气动载荷分布和翼尖涡的角度探讨了变体翼梢小翼相对传统翼梢小翼的优缺点.结果表明:在飞机的起飞阶段,变体翼梢小翼的减阻效率比传统翼梢小翼高2.2%,同时将翼尖涡强度降低了15%,有利于提高飞机的燃油效率和机场空域安全;但也会增大机翼的翼根弯矩,因此必须权衡变体翼梢小翼带来的气动收益与结构强度不利因素.     

基于全局线性稳定性分析的翼尖双涡不稳定特征演化机理

相比于机翼产生的孤立翼尖涡,加装小翼之后的翼尖涡表现出双涡甚至多涡结构,并且呈现出更加复杂的不稳定特征。为揭示翼尖双涡结构不稳定特征及其演化机理,采用体视粒子图像测速（SPIV）技术和全局线性稳定性分析（LAS）方法对不同雷诺数和攻角下带双叉弯刀小翼的M6机翼产生的翼尖涡结构在尾迹区的不稳定特征进行研究。试验结果表明,对称布置的双叉弯刀小翼产生的翼尖涡包含上/下小翼产生的主涡（上/下主涡）结构,两者构成近似等强度的同转涡对,在相互靠近的同时以20 rad/s的角速度相互缠绕。对上/下主涡瞬时涡核位置的统计分析表明,翼尖涡摇摆幅值随流向位置逐渐增大,随雷诺数的增加而增大,随攻角的增加先增大后减小。对16倍弦长的尾迹截面处的翼尖双涡结构进行全局时间稳定性分析,不同工况下,上/下主涡最不稳定模态（模态P/模态S）的稳定性曲线变化规律与摇摆幅值的变化规律相一致,表明翼尖涡的摇摆源自于其内在的不稳定性特征。增加流向扰动波数,发现模态P切向波数逐渐增加;而模态S则是径向波数逐渐增加。不同工况下,模态P的切向波数为5~6,扰动波数分布在[2.75,5]的区间内,所对应的不稳定放大率均大于模态S,而不稳定放大率最大的模态扰动范围作用在上主涡的整个涡核区域,表明这种大切向波数的扰动模态在翼尖涡流控中的潜在价值,也意味着加装小翼会增加涡结构的个数,增强不稳定性的发展,有助于翼尖涡的快速失稳衰减。     

Numerical study of aircraft wake vortex evolution near ground in stable atmospheric boundary layer

The evolutions of aircraft wake vortices near ground in stable atmospheric boundary layer are studied by Large Eddy Simulation(LES). The sensitivity of vortex evolution to the Monin-Obukhov(M-O) scale is studied for the first time. The results indicate that increasing stability leads to longer lifetimes of upwind vortices, while downwind vortices will decay faster due to a stronger crosswind shear under stable conditions. Based on these results, an empirical model of the vortex lifetime as a function of 10-m-high crosswind and the M-O scale is summarized. This model can provide an estimate of the upper boundary of the vortex lifetime according to the realtime crosswind and atmospheric stability. In addition, the lateral translation of vortices is also inspected. The results show that vortices can travel a furthest distance of 722 m in the currentlystudied parameter range. This result is meaningful to safety analysis of airports that have parallel runways.     

Wake vortex characteristics of transport aircraft

The flow and flight physics of wake vortex systems has been intensively investigated concentrating on a large variety of aspects. This paper gives a brief overview on past and present wake vortex research activities such as early studies, integrated programs, model and flight tests, numerical investigations, fundamental physical aspects and alleviation strategies. Then, detailed results of the properties of the wake near field and extended near field are presented addressing typical length and time scales and especially turbulence quantities. Progressing from the near field to the far field wake instability mechanisms are explained along with their relevance for wake vortex decay. Characteristic quantities are given for the short and long wave instabilities associated with vortex merging and wakes consisting of two and four trailing vortices. A non-dimensional frequency parameter is introduced to classify the main instability types. Means for wake vortex alleviation are described aimed at influencing the wake vortex turbulence field or triggering and amplifying the inherent instabilities. The methods discussed include passive means such as the effects of spoilers, differential flap setting and four-vortex systems and active means using oscillating flaps or auxiliary devices.     

亚声速全机纵横向气动特性计算方法

本文介绍了一种涡格方法,它适用于亚声速飞机的纵横向气动特性计算。该方法中,升力面用布置在中弧面的平均平面上的单涡格层,或用布置在上、下表面的平均平面上的双涡格层模拟,机身则由布置在表面上的四边形涡环或由布置在一组同轴棱柱面上的涡栅来模拟。地面效应用布置镜像涡系的办法处理。文中讨论了机翼尾涡偏斜对平尾、立尾的影响。 该方法计算的结果与有关的理论和实验进行了比较。这些比较表明,此方法计算精度满足工程设计的要求。     

Review of flow control mechanisms of leading-edge vortices

Vortex control concepts employed for slender and nonslender delta wings were reviewed. Important aspects of flow control include flow separation, vortex formation, flow reattachment, vortex breakdown, and vortex instabilities. The occurrence and relative importance of these phenomena strongly depend on the wing sweep angle. Various flow control methods were discussed: multiple vortices, control surfaces, blowing and suction, low-frequency and high-frequency excitation, feedback control, passive control with wing flexibility, and plasma actuators. For slender delta wings, control of vortex breakdown is achieved by modifications to swirl level and external pressure gradient acting on the vortex core. Effects of flow control methods on these two parameters were discussed, and their effectiveness was compared whenever possible. With the high-frequency excitation of the separated shear layer, reattachment and lift enhancement in the post-stall region is observed, which is orders of magnitude more effective than steady blowing. This effect is more pronounced for nonslender wings. Re-formation of vortices is possible with sufficient amplitude of forcing at the optimum frequency. Passive lift enhancement on flexible wings is due to the self-excited wing vibrations, which occur when the frequency of wing vibrations is close to the frequency of the shear layer instabilities, and promote flow reattachment.     

空中交通中尾流间隔的研究

分析了雷达尾流间隔标准的分类，通过尾流的形成机理和对后机影响的分析，建立了后机的危险遭遇模型和前机的尾流消散模型，给出了在确定的时间间隔下确定尾流危险遭遇概率的方法。     

Equilibrium state of trailing vortices: two-dimensional model of a far-field vortex wake

The equilibrium statistical mechanics of a system composed of a large number of two-dimensional point vortices is employed to describe the vortex system shed from aircraft wings. According to this theory, these higher energy states of the vortex system can only be achieved by segregating the point vortices of like kind into two clusters that descend with a constant velocity. The solution is given in terms of the integral constraints for each cluster: total circulation, center of inertia, and kinetic energy. The negative non-dimensional inverse temperature of the system and the length scale related to angular momentum of a single trailing vortex are obtained versus initial interaction energy of the vortex system. Comparison of the theoretical results with available experimental data shows good agreement between the calculated tangential velocity distribution in the trailing vortex and the data. The flow characteristics for three different wing loads are also compared to emphasize the effect of initial circulation distribution along a lifting wing on the vorticity distribution in the equilibrium trailing vortices.