Large eddy simulation of aircraft wake vortex with self-adaptive grid method

A self-adaptive-grid method is applied to numerical simulation of the evolu- tion of aircraft wake vortex with the large eddy simulation （LES）. The Idaho Falls （IDF） measurement of run 9 case is simulated numerically and compared with that of the field experimental data. The comparison shows that the method is reliable in the complex atmospheric environment with crosswind and ground effect. In addition, six cases with different ambient atmospheric turbulences and Brunt V^iis/il^i （BV） frequencies are com- puted with the LES. The main characteristics of vortex are appropriately simulated by the current method. The onset time of rapid decay and the descending of vortices are in agreement with the previous measurements and the numerical prediction. Also, sec-ondary structures such as baroclinic vorticity and helical structures are also simulated. Only approximately 6 million grid points are needed in computation with the present method, while the number can be as large as 34 million when using a uniform mesh with the same core resolution. The self-adaptive-grid method is proved to be practical in the numerical research of aircraft wake vortex.

Study on the Influence of a Wake Vortex on an ARJ21 Aircraft Using the Strip Method

A model for the vortex distribution in the wake of an aircraft is elaborated to investigate the wake influence on the behaviour of other aircrafts potentially interacting with it.As a realistic case,the interaction of an ARJ21 aircraft with a(leading)A330-200 aircraft is considered.Different distances are considered,namely,6 km,7 km,8 km,9.3 km,and 10 km.Simulations based on the used wake dissipation mechanism are used to investigate different conditions,namely,the ARJ21 in take-off and level flight and the changes induced in the related lift by the front aircraft A330-200 during landing.The induced roll moment is also studied and analyzed by means of a strip method.As a result,the roll moment coefficient is determined to quantify the roll degree of the aircraft when it is influenced by the wake vortex.The results show the overall roll moment coefficient of the considered ARJ21 aircraft is less than 0.05,and the wing roll moment coefficient is less than 0.04.Such results are interpreted and discussed according to existing standards.

Large eddy simulation of cloud cavitation and wake vortex cavitation around a trailing-truncated hydrofoil

The cavitation has received considerable attention for decades because of its negative influence on the performance and the safety of the hydraulic machinery.In this study,a large eddy simulation is carried out to numerically investigate the unsteady cavitating flow around a trailing-truncated NACA 0009 hydrofoil for determining the underlying physical mechanisms.Two types of cavitation morphologies are identified:The large-scale bubble cluster and the von Kármán vortex cavity,named as the cloud cavitation and the wake vortex cavitation,respectively.It is shown that the velocity profiles obtained over the hydrofoil suction surface are in good agreement with the experimental data,indicating the accuracy of the current simulation.The dynamic evolution of the sheet/cloud cavity is also well reproduced,covering the sheet cavity breakup,the sheet/cloud transformation,and the collapse of the cloudy bubble cluster.The wake-vortex cavitation is caused by the blunt geometry at the hydrofoil trailing edge,where pairs of vortex cavities are induced.Both the cloud and vortex cavities significantly affect the lift oscillation,which makes it difficult to decompose the components.The fundamental shedding mechanisms of the wake vortex cavitation are discussed based on the finite-time Lyapunov exponent field.Specifically,the suction-side bubble grows and squeezes the giant pressure bubble away from the trailing edge.After the pressure bubble detaches,a new counterclockwise vortex or a new bubble appears at the pressure side,thus lifting the ridge towards the suction trailing edge and generating a strong vortex eye that pinches off the trailing portion of the suction-side bubble.

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 evolution, 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.

NUMERICAL STUDY OF PARTICLE DISTRIBUTION IN WAKE OF LIQUID-PARTICLE FLOWS PAST A CIRCULAR CYLINDER USING DISCRETE VORTEX METHOD

Particle-laden water flows past a circular cylinder were numerically investigated. The discrete vortex method （DVM） was employed to evaluate the unsteady water flow fields and a Lagrangian approach was applied for tracking individual solid particles. A dispersion function was defined to represent the dispersion scale of the particle. The wake vortex patterns, the distributions and the time series of dispersion functions of particles with different Stokes numbers were obtained. Numerical results show that the particle distribution in the wake of the circular cylinder is closely related to the particle＇s Stokes number and the structure of wake vortices： （1） the intermediate sized particles with Stokes numbers, St, of 0.25, 1.0 and 4.0 can not enter the vortex cores and concen- trate near the peripheries of the vortex structures, （2） in the circular cylinder wake, the dispersion intensity of particles decreases as St is increased from 0.25 to 4.0.

A Novel Wake Oscillator Model for Vortex-Induced Vibrations Prediction of A Cylinder Considering the Influence of Reynolds Number

It is well known that the Reynolds number has a significant effect on the vortex-induced vibrations(VIV) of cylinders. In this paper, a novel in-line(IL) and cross-flow(CF) coupling VIV prediction model for circular cylinders has been proposed, in which the influence of the Reynolds number was comprehensively considered. The Strouhal number linked with the vortex shedding frequency was calculated through a function of the Reynolds number. The coefficient of the mean drag force was fitted as a new piecewise function of the Reynolds number, and its amplification resulted from the CF VIV was also taken into account. The oscillating drag and lift forces were modelled with classical van der Pol wake oscillators and their empirical parameters were determined based on the lock-in boundaries and the peak-amplitude formulas. A new peak-amplitude formula for the IL VIV was developed under the resonance condition with respect to the mass-damping ratio and the Reynolds number. When compared with the results from the experiments and some other prediction models, the present model could give good estimations on the vibration amplitudes and frequencies of the VIV both for elastically-mounted rigid and long flexible cylinders. The present model considering the influence of the Reynolds number could generally provide better results than that neglecting the effect of the Reynolds number.

Modelling of the Vortex-Induced Motion of A Single-Column Platform with Non-Linear Mooring Stiffness Using the Coupled Wake Oscillators

A phenomenological model for predicting the vortex-induced motion (VIM) of a single-column platform with non- linear stiffness has been proposed. The VIM model is based on the couple of the Duffing-van der Pol oscillators and the motion equations with non-linear terms. The model with liner stiffness is presented for comparison and their results are compared with the experiments in order to calibrate the model. The computed results show that the predicted VIM amplitudes and periods of oscillation are in qualitative agreements with the experimental data. Compared with the results with linear stiffness, it is found that the application of non-linear stiffness causes the significant reductions in the in-line and transverse motion amplitudes. Under the non-linear stiffness constraint, the lock-in behavior is still identified at 8<Ur<15, and the trajectories of the VIM on the xy plane with eight-figure patterns are maintained. The results with different non-linear geometrically parameters show that both in-line and transverse non-linear characteristics can significantly affect the predict in-line and transverse motion amplitudes. Furthermore, the computed results for different aspect ratios indicate that the in-line and transverse motion amplitudes increase with the growth of aspect ratio, and the range of lock-in region is enlarged for the large aspect ratio.

WAKE GEOMETRY CALCULATIONS FOR TILT-ROTOR USING VISCOUS VORTEX METHOD

A tilt-rotor unsteady flow analytical method has been developed based upon viscous vortex-particle method.In this method,the vorticity field is divided into small assembled vortex particles.Vortex motion and diffusion are obtained by solving the velocity-vorticity-formed incompressible Navier-Stokes equations using agrid-free Lagrangian simulation method.Generation of the newly vortex particles is calculated by using the Weissinger-L lifting surface model.Furthermore,in order to significantly improve computational efficiency,a fast multiple method(FMM)is introduced into the calculation of induced velocity and its gradient.Finally,the joint vertical experimental(JVX)tilt-rotor is taken as numerical examples to analyze.The wake geometry and downwash are investigated for both hover and airplane modes.The proposed method for tilt-rotor flow analysis is verified by comparing its results with those available measured data.Comparison indicates that the current method can accurately capture the complicated tilt-rotor wake variation and be suitable for aerodynamic interaction simulation in complex environments.Additionally,the aerodynamic interactional characteristics of dual-rotor wake are discussed in different rotor distance.Results show that there are significant differences on interactional characteristics between hover mode and airplane mode.

Study on the Wake Shape behind a Wing in Ground Effect Using an Unsteady Discrete Vortex Panel Method

The unsteady evolution of trailing vortex sheets behind a wing in ground effect is simulated using an unsteady discrete vortex panel method. The ground effect is included by image method. The present method is validated by comparing the simulated wake roll-up shapes to published numerical results. When a wing is flying in a very close proximity to the ground, the optimal wing loading is parabolic rather than elliptic. Thus, a theoretical model of wing load distributions is suggested, and unsteady vortex evolutions behind lifting lines with both elliptic and parabolic load distributions are simulated for several ground heights. For a lifting line with elliptic and parabolic loading, the ground has the effect of moving the wingtip vortices laterally outward and suppressing the development of the vortex. When the wing is in a very close proximity to the ground, the types of wing load distributions does not affect much on the overall wake shapes, but parabolic load distributions make the wingtip vortices move more laterally outward than the elliptic load distributions.

基于激光雷达探测的飞机尾流融合预测方法

为提高基于激光雷达的飞机尾流探测反演精度,根据扫描出的径向风速数据,建立了基于Kolmogorov结构函数的大气背景湍流耗散率(EDR)估计方法;然后基于两阶段消散预测模型,计入湍流对尾流消散过程的影响,实现基于历史探测数据的尾涡强度环量和涡核运动趋势的预测;通过环境探测数据与预测模型的结合,提高尾涡特性参数的反演精度。研究表明,相较于反演算法,采用本文模型预测的尾涡轨迹在径向距离和角度的精度上分别提高了59.5%、64.8%。

不同B-V频率下的飞机尾涡数值模拟研究

为保障民航飞机的运行安全,探究大气分层对飞机尾涡的影响,对不同B-V频率和初始温度条件下的尾流演化进行研究。选择SST k-ω湍流模型,使用Fluent软件对自定义函数搭建的9种大气环境下的A333飞机尾涡演化进行数值模拟,并基于演化结果对飞行安全进行分析。结果表明:初始温度不同主要会引起尾涡初始强度的不同,但对尾涡发展影响较小。B-V频率主要作用于t′=1.5之后,使尾涡特征的演化产生差异。较大的B-V频率会诱使尾涡上方产生小尺度的次级涡旋,加速尾涡衰减,减小涡核间距。B-V频率的增大会引起尾涡下沉速率大幅减小,使前机尾流在后机的飞行航路上停留更久,从而增大尾流间隔。

基于时间间隔标准的尾流安全评估分析方法

科学地优化飞机间尾流间隔是提升机场吞吐量的重要举措,确保安全是尾流间隔实施的首要前提。首先,基于大涡模拟试验数据,对经典的两阶段消散模型(Wake Two-Stage Decay Model,D2P)模型进行改进,创建顶风对尾涡环量衰减的影响模型。然后,针对基于时间间隔(Time-Based Separation,TBS)未考虑顶风会影响尾涡移动和尾涡环量衰减,通过转化为飞机地速和构建改进D2P模型深刻分析两因素对尾涡遭遇严重度的影响。最后,计算实施TBS时不同风速不同机型组合对应的最小尾流间隔,并综合分析对应间隔的尾涡遭遇严重度。结果表明:虽然TBS未考虑顶风对尾涡移动和环量衰减的影响,但可以确保前后机安全性;在顶风8 m/s应用TBS方案时,各机型组合的尾涡遭遇严重度约为静风时的30%。TBS安全地缩减了顶风时的尾流间隔。

基于POD和DMD的60°交叉管绕流分析

本文利用本征正交分解(Proper Orthogonal Decomposition,POD)和动力学模态分解(Dynamic Mode Decom⁃position,DMD)分析雷诺数Re=200时三维60°交叉管在间隙比G=4下的涡量数据,并探究尾涡的演变规律。分析结果表明:尾流场中的涡流尺度及重要程度随频率增加而减小,少数低频模态便可主导大尺度流动现象,而高频模态主要丰富尾流场中的小尺度湍流细节;上下游圆柱的涡结构以0.19 Hz的频率从两圆柱脱落,并在相同的频率下以平行形态向下游演变;上游圆柱脱落涡与下游圆柱的相互作用导致下游圆柱涡激振动明显,并产生多个高频升力频谱峰值。

尾流冲浪中后机等效诱导升力计算分析

为进一步得到在尾流冲浪中的减阻、节油等效益,提出了一种尾流冲浪中后机获取升力的计算方法,对节油率进行分析。采取数值模拟的方法,选取A330-200机型作为前机和后机,以其适用巡航速度在高空飞行作为背景,模拟了其尾涡的环量、半径以及其产生的下沉运动。根据尾流的耗散规律从2000~4500 m范围中选取了6组前后机纵向间隔,参照不同的后机距涡核的相对位置进行了滚转力矩分析,根据诱导速度等效转化为后机均匀获取的诱导升力,分析评估出合理的后机冲浪位置,得出较高的节油率为12.28%。

基于尾流振子模型的柔性悬挂立管涡激振动分析

为了分析深海采矿柔性立管涡激振动响应特性,提出了一种高效的针对特殊边界的处理方法.基于欧拉梁模型和尾流振子模型,结合有限差分方法,系统研究不同边界条件、中间仓质量和海流剪切参数对深海采矿立管涡激振动的影响规律.结果表明:悬挂立管底部会产生较大位移,与传统两端铰接立管相比,相同激励下悬挂立管会激发出更高阶的振动模态,从原本5阶模态升至6阶;随着中间仓质量增加,立管振动的主导模态会随之降低,在同一模态下,悬挂立管底部位移逐渐减小,从0.460降至0.405,当模态转换时,底部位移均方根会迅速增大,由0.405升至0.413;底部位移随着均匀流速的增加呈现出波动趋势,在一定流速范围内,位移随流速线性变化;随着剪切参数增大,在同一模态下,立管底部的位移逐渐减小,当模态转换时,底部位移会增加.

串列三圆柱流固耦合响应的尾流干涉与动态演变特性研究

基于有限体积法应用开源OpenFOAM软件对串列三圆柱的涡激振动响应进行了数值模拟研究,分析了雷诺数Re=150、间距比介于2~6的串列三圆柱在约化速度2~16范围内的流固耦合动态响应特性.研究观察到:当间距比为2时,上游圆柱振动锁定的区域明显变宽,并且在锁定区域内振幅明显高于大间距工况,表明小间距布置时,下游圆柱的存在对上游圆柱振动起增强作用.由于尾流诱导的作用,中间圆柱和下游圆柱振幅的最大值高于上游圆柱.串列三圆柱的尾流干涉模式存在拓展体模式、持续再附着模式、交替再附着模式、拟同脱落模式和同脱落模式5种,并且由于圆柱振动过程中振幅的动态变化,尾流干涉模式出现不稳定切换.在间距比为2,约化速度为7时观察到振动存在“拍”现象,在间距比为6,约化速度为4时观察到多频参与振动的大周期现象,两种现象发生时都会引起柱体升力和振幅的波动.当中间圆柱和下游圆柱的尾流干涉处于拟同脱落模式时,尾迹中的双排涡合并形成二次涡街,而双排涡的融合发生在同侧相邻的两个旋涡或3个旋涡之间,与圆柱的间距比相关.

考虑四极子声源的高速磁浮列车气动噪声数值模拟方法

随着列车速度的提高,四极子声源对列车气动噪声的贡献增大,高速磁浮列车的运行速度达到600 km/h时,有必要考虑四极子声源对高速磁浮列车气动噪声的影响.为此,本文建立考虑四极子声源的高速磁浮列车气动噪声数值模拟方法,对高速磁浮列车流线型尾部、头部区域的积分面进行局部外推,探索流线型尾部、头部区域的四极子声源对高速磁浮列车气动噪声的影响.研究发现:高速磁浮列车的尾涡会穿过下游的积分面,流线型尾部区域不能采用全封闭积分面,否则会产生非常大的伪声;流线型尾部区域的积分面需要较多地向尾涡区延伸,并去除尾涡穿过的区域;高速磁浮列车流线型头部区域四极子声源的贡献很小,流线型头部区域的积分面可以取为流线型头型表面;在600 km/h下,高速磁浮列车四极子声源引起的气动噪声能量占比达到42%.

涡流恢复导叶对螺旋桨气动和声学性能影响研究

为了对比安装涡流恢复导叶与单排螺旋桨气动性能和气动噪声的差异,采用数值模拟的方法研究了安装六种不同间距涡流恢复导叶和单排螺旋桨的气动力及气动噪声。研究结果表明:在起飞状态,级间距Δx=0.27的工况下,安装涡流恢复导叶使得推力系数增加6.4%,效率增加6.7%。随着间距的增大,前级叶片的桨尖涡、尾迹涡等涡系结构在通过后级叶片时破碎并向下游传播,且强度逐渐减小。噪声强度随着级间距的增加而逐渐减小,最大级间距涡流恢复导叶的噪声与最小级间距涡流恢复导叶噪声相比降低5.7 dB,噪声下降幅度随级间距的增加逐渐减缓,存在级间距最优位置使得推力增加最大,噪声强度适中。

潜艇围壳填角几何外形的水动力特性研究

围壳填角几何外形对潜艇水动力特性有重要影响。基于SUBOFF全附体潜艇模型,采用RNG k-ε湍流模型对含有3种不同类型围壳填角的SUBOFF潜艇绕流场进行数值计算,研究围壳填角几何外形对围壳附近马蹄涡的产生、强度以及潜艇尾部伴流场的影响。结果表明,平滑过度的围壳填角有效抑制了马蹄涡的产生,降低了潜艇尾部伴流流向速度分量的不均匀度;含凸型围壳填角的潜艇模型达到的效果最优,其在尾部伴流场处流向速度分量不均匀度的最高下降幅度为24.5%。

Evolution of vortices in the wake of an ARJ21 airplane: Application of the lift-drag model

Wake separation is crucial to aircraft landing safety and is an important factor in airport operational efficiency.The near-ground evolution characteristics of wake vortices form the foundation of the wake separation system design.In this study,we analysed the near-ground evolution of vortices in the wake of a domestic aircraft ARJ21 initialised by the lift-drag model using large eddy simulations based on an adaptive mesh.Evolution of wake vortices formed by the main wing,flap and horizontal tail was discussed in detail.The horizontal tail vortices are the weakest and dissipate rapidly,whereas the flap vortices are the strongest and induce the tip vortex to merge with them.The horizontal tail and flap of an ARJ21 do not significantly influence the circulation evolution,height change and movement trajectory of the wake vortices.The far-field evolution of wake vortices can therefore be analysed using the conventional wake vortex model.