A STUDY ON THE MECHANISM OF HIGH-LIFT GENERATION BY AN AIRFOIL IN UNSTEADY MOTION AT LOW REYNOLDS NUMBER

The aerodynamic force and flow structure of NACA 0012 airfoil performing an unsteady motion at low Reynolds number (Re = 100) are calculated by solving Navier-Stokes equations. The motion consists of three parts: the first translation, rotation and the second translation in the direction opposite to the first. The rotation and the second translation in this motion are expected to represent the rotation and translation of the wing-section of a hovering insect. The flow structure is used in combination with the theory of vorticity dynamics to explain the generation of unsteady aerodynamic force in the motion. During the rotation, due to the creation of strong vortices in short time, large aerodynamic force is produced and the force is almost normal to the airfoil chord. During the second translation, large lift coefficient can be maintained for certain time period and (C) over bar (L), the lift coefficient averaged over four chord lengths of travel, is larger than 2 (the corresponding steady-state lift coefficient is only 0.9). The large lift coefficient is due to two effects. The first is the delayed shedding of the stall vortex. The second is that the vortices created during the airfoil rotation and in the near wake left by previous translation form a short 'vortex street' in front of the airfoil and the 'vortex street' induces a 'wind'; against this 'wind' the airfoil translates, increasing its relative speed. The above results provide insights to the understanding of the mechanism of high-lift generation by a hovering insect.

Surface integral analogy approaches for predicting noise from 3D high-lift low-noise wings

Three surface integral approaches of the acoustic analogies are studied to predict the noise from three concep- tual configurations of three-dimensional high-lift low-noise wings. The approaches refer to the Kirchhoff method, the Ffowcs Williams and Hawkings （FW-H） method of the permeable integral surface and the Curle method that is known as a special case of the FW-H method. The first two approaches are used to compute the noise generated by the core flow region where the energetic structures exist. The last approach is adopted to predict the noise specially from the pressure perturbation on the wall. A new way to con- struct the integral surface that encloses the core region is proposed for the first two methods. Considering the local properties of the flow around the complex object-the actual wing with high-lift devices-the integral surface based on the vorticity is constructed to follow the flow structures. The surface location is discussed for the Kirchhoff method and the FW-H method because a common surface is used for them. The noise from the core flow region is studied on the basis of the dependent integral quantities, which are indicated by the Kirchhoff formulation and by the FW-H formulation. The role of each wall component on noise contribution is analyzed using the Curle formulation. Effects of the volume integral terms of Lighthill＇s stress tensors on the noise pre-diction are then evaluated by comparing the results of the Curle method with the other two methods.

Numerical study of the influence of spoiler deflection on high-lift configuration

This paper numerically studies the influence of the downward spoiler deflection on the boundary layer flow of a high-lift two-element airfoil consisting of a droop nose, a main wing, a downward deflecting spoiler and a single slotted flap. Both of the boundary layer of the upper surface of the spoiler and the confluent boundary layer of the upper surface of the flap become thicker, as the downward spoiler deflection increases. Compared to the attached flow at the angle of attack of 10°, the flow of the upper surface of the spoiler becomes separated at the angle of attack of 16° when the spoiler deflection is large enough, which corresponds to the boundary layer flow reversal in velocity profiles.

Dynamic Stall on High-Lift Airfoil 30P30N in Ground Proximity

Computational prediction of stall aerodynamics in free air and in close proximity to the ground considering the 30P30N three-element high-lift configuration is carried out based on CFD simulations using the OpenFOAM code and Fluent software. Both the attached and separated flow regimes are simulated using the Reynolds Averaged Navier-Stokes (RANS) equations closed with the Spalart-Allamaras (SA) turbulence model for static conditions and pitch oscillations at Reynolds number, Re = 5 x 106 and Mach number, M = 0.2. The effects of closeness to the ground and dynamic stall are investigated and the reduction in the lift force in close proximity to the ground is discussed.

A novel hybrid method for aerodynamic noise prediction of high-lift devices

Aerodynamic noise of High-Lift Devices(HLDs)is one of the main sources of airframe noise,and has immediate impacts on the airworthiness certification,environmental protection and security of commercial aircraft.In this study,a novel hybrid method is proposed for the aerodynamic noise prediction of HLD.A negative Spalart-Allmaras(S-A)turbulence model based Improved Delayed Detached Eddy Simulation(IDDES)method coupling with AFT-2017b transition model is developed,in order to elaborately simulate the complex flow field around the HLD and thus obtain the information of acoustic sources.A Farassat-Kirchhoff hybrid method is developed to filter the spurious noise sources caused by the vortex motions in solving the Ffowcs Williams-Hawkings(FW-H)equation with permeable integral surfaces,and accurately predict the far-field noise radiation of the HLD.The results of the 30P30N HLD indicate that,the computational Sound Pressure Levels(SPLs)obtained by the Farassat-Kirchhoff hybrid method conform well with the experimental ones in the spectrum for the given observation point,and are more accurate than those obtained by the Farassat 1A method.Based on the hybrid method,the acoustic directivity of the HLD of a commercial aircraft is obtained,and the variation of the SPLs in the spectrum with the deflection angle of the slat is analyzed.

高扬程泵站虹吸式出水流道虹吸形成过程分析

为研究高扬程泵站虹吸式出水流道虹吸形成过程,以某高扬程泵站的出水流道及出水池为研究对象,建立三维模型并使用Fluent仿真计算了虹吸管流态变化。针对3种出水池水位使用VOF模型计算其压力、流速等参数。驼峰段原角度为段前150°、段后160°,在虹吸段顶端使用DN350的真空破坏阀,同时改变驼峰段角度进行优化,发现将段前角度增加10°后,虹吸形成时间为448 s,相较于优化前缩短了56 s,改善了泵启动过程。分析发现,不同水位下虹吸形成时压力分布较为均匀;水位较低时流速分布不均,不良流态产生,低水位造成的负面影响远大于高水位;在驼峰段安装DN350真空阀能减小水力损失,对虹吸形成过程起到促进作用;真空阀会影响经典断面处流速分布,产生高流速区,出水池水位较低时,该现象使得流速分布不均。

榆树林油田CCUS采油工程方案优化设计与实践

大庆榆树林油田扶杨油层属低孔、特低渗透储层,针对以往开发过程中存在注水困难、压裂有效期短、水驱开发难以有效动用的问题,开展CO_(2)驱油技术现场试验。从经济性、技术适应性、配套工艺成熟性等角度对采油工程方案进行综合评价,优选出单、双管分层注入工艺、高气液比举升工艺、注采两端个性化防腐工艺及物理化学组合解冻堵工艺等CCUS采油工程技术。结果表明:试验区投产初期及目前生产情况均达到了油藏预测指标;采出井平均泵效及检泵周期与外围油田平均水平相持平,注气井与采出井腐蚀速率小于行业指标;实现CO_(2)有效埋存108.9×10^(4) t,比水驱预测采出程度提高采收率4.39百分点,取得较好的驱油开发效果。研究成果为CCUS示范区的高效建设提供了技术支撑,开辟了大庆油田外围难采储量有效动用的新途径。

YKJ-01型附着式升降脚手架在330m超高层建筑的应用

针对某330 m超高层项目,详细介绍了附着式升降脚手架在超高层的应用,主要包括:附着式升降脚手架施工平面布置,附着式升降脚手架参数设计,附着式升降脚手架直爬与斜爬部位处理,建筑结构凹槽位置防护设计,附着式升降脚手架斜爬角度变化,避难层位置附着式升降脚手架处理,高区大堂处格构柱设计,塔式起重机附墙处附着式升降脚手架处理措施,施工电梯处附着式升降脚手架处理措施,卸料平台处附着式升降脚手架处理措施,附着式升降脚手架分片提升断口位置处理,附着式升降脚手架安装、提升、拆除等。

大型客机机体噪声机理及控制技术

气动噪声问题不仅是大型客机适航取证的关键技术难题,更是关系到乘客舒适度的重要技术指标。增升装置噪声和起落架噪声是大型客机机体噪声的主要来源。本文针对我国大型客机研制中增升装置噪声和起落架噪声的产生机理及控制关键科学问题,开展噪声源、远场声辐射精细化数值模拟。针对噪声产生机理,发展了近壁面边界涡量流、拟涡能流等涡动力学过程与涡声理论相结合的噪声源分析方法;针对机体噪声控制难题,提出了缝翼凹腔小尺度波纹噪声控制方法和起落架支杆大尺度波纹噪声控制方法。数值模拟结果表明:缝翼凹腔是增升装置的重要噪声源之一;中低频噪声和纯音峰值主要来自缝翼凹腔和主翼前缘,后缘襟翼对噪声的贡献相对较小;起落架尾迹区域和轮胎空腔区域存在大量、复杂的大尺度湍流涡结构,是起落架的主要噪声源,起落架各部件噪声特性基本呈现宽频特性,支柱部件辐射噪声最大,轮胎次之,中间的连轴部件和扭杆部件辐射噪声相对较小;缝翼凹腔波纹噪声控制方法兼具减阻和降噪功效;起落架大尺度波纹噪声控制方法能有效降低远场辐射噪声。本文研究内容可为增升装置气动与噪声一体化设计、起落架降噪设计等提供技术支撑。

High-Lift Effect of Bionic Slat Based on Owl Wing

A slat without a cove is built on the basis of a bionic airfoil （i.e. stowed multi-element airfoil）, which is extracted from a long-eared owl wing. The three-dimensional models with a deployed slat and a stowed slat are measured in a low-turbulence wind tunnel. The results are used to characterize high-lift effect： compared with the stowed slat, the deployed slat works more like a spoiler at low angles of attack, but like a conventional slat or slot at high angles of attack. In addition, it can also increase stall angle and maximum lift coefficient, and postpone the decrease in the gradient of the lift coefficient. At the same time, the flow field visualized around both three-dimensional models suggests the leading-edge separation associated with the decrease in the gradient of the lift coefficient, Furthermore, the related two-dimensional simulation well agrees with the analysis of the lift coefficient, as the complement to the experiment. The bionic slat may be used as reference in the design of leading-edge slats without a cove.

Profile and Secondary Flow Losses in a High-Lift LPT Blade Cascade at Different Reynolds Numbers under Steady and Unsteady Inflow Conditions

The aerodynamic flow field downstream of a Low-Pressure High-Lift(HL)turbine cascade has been experimentally investigated for different Reynolds numbers under both steady and unsteady inflows,in order to analyse the cascade performance under real engine operating conditions.The Reynolds number has been varied in the range 100000<Re<300000,where lower and upper limits are typical of cruise and take-off/landing conditions,respectively.The effects induced by the incoming wakes at the reduced frequency f+=0.62 on both profile and secondary flow losses have been investigated.Total pressure,velocity and secondary kinetic energy distributions at the downstream tangential plane have been measured by means of a miniaturized 5-hole probe.These quantities provide information on both blade wake and secondary flow structures(passage and horse-shoe vortices).The analysis of the results allows the evaluation of the aerodynamic performance of the HL front-loaded blade in terms of both profile and secondary losses.

Aerodynamic performance enhancement of co-flow jet airfoil with simple high-lift device

The present study performed a numerical investigation to explore the performance enhancement of a co-flow jet(CFJ)airfoil with simple high-lift device configuration,with a specific goal to examine the feasibility and capability of the proposed configuration for low-speed take-off and landing.Computations have been accomplished by an in-house-programmed Reynoldsaveraged Navier-Stokes solver enclosed by k-ωshear stress transport turbulence model.Three crucial geometric parameters,viz.,injection slot location,suction slot location and its angle were selected for the sake of revealing their effects on aerodynamic lift,drag,power consumption and equivalent lift-to-drag ratio.Results show that using simple high-lift devices on CFJ airfoil can significantly augment the aerodynamic associated lift and efficiency which evidences the feasibility of CFJ for short take-off and landing with small angle of attack.The injection and suction slot locations are more influential with respect to the aerodynamic performance of CFJ airfoil compared with the suction slot angle.The injection location is preferable to be located in the downstream of the pressure suction peak on leading edge to reduce the power expenditure of the pumping system for a relative higher equivalent lift-to-drag ratio.Another concluded criterion is that the suction slot should be oriented on the trailing edge flap for achieving more aerodynamic gain,meanwhile,carefully selecting this location is crucial in determining the aerodynamic enhancement of CFJ airfoil with deflected flaps.

Unsteady wakes-secondary flow interactions in a high-lift low-pressure turbine cascade

Detailed experimental measurements were conducted to study the interactions between incoming wakes and endwall secondary flow in a high-lift Low-Pressure Turbine(LPT)cascade.All of the measurements were conducted in both the presence and absence of incoming wakes,and numerical analysis was performed to elucidate the flow mechanism.With increasing Reynolds number,the influence of the incoming wakes on suppressing the secondary flow gradually increased owing to the greater influence of incoming wakes on reducing the negative incidence angle at higher Reynolds numbers,leading to a lower blade loading near the leading edge and suppression of the Pressure Side(PS)leg of the horseshoe vortex.However,the effect of unsteady wakes on suppressing the profile losses gradually became weaker owing to the reduced size of the Suction Side(SS)separation bubble and increased mixing loss in the free-flow region at high Reynolds numbers.Incoming wakes clearly improved the aerodynamic performance of the low-pressure turbine cascade at low Reynolds numbers of 25,000 and 50,000.In contrast,at the high Reynolds number of 100,000,the profile loss at the midspan and mass-averaged total losses downstream of the cascade were higher in the presence of wakes than in the absence of wakes,and the unsteady wakes exerted a negative influence on the aerodynamic performance of the LPT cascade.

Investigation of water impingement on a multi-element high-lift airfoil by Lagrangian and Eulerian approach

McDonnell Douglas Aerospace(MDA)high-lift model is widely used in the study of multi-element airfoil,while there is still short knowledge of ice accretion and water impingement on it.In this paper,based on two-phase flow theory,two numerical models were presented by using both Eulerian approach and Lagrangian approach,respectively,in order to predict the water impingement efficiency on a two-dimensional(2D)multi-element high-lift airfoil.Both computational results were validated with the experiment data,which shown good agreements in the impingement limitations and tendency.The trend that how the attack angle and droplet diameter affect the feather of local water impingement characteristics on the different elements of MDA were further investigated.As shown in this research,the trends that the local impingement intensity and extent on flap of MDA varied differently as in general understanding due to the complex structures of flow field,which should be careful cognized in design of the ice protection system.

High-lift siphon flow velocity in a 4-mm siphon hose

High-lift siphon drainage by 4-mm internal diameter siphon hoses is a real-time, free-power, and long-term approach for slope drainage. The conventional hydraulics formula for pressurized pipe flow is generally used to calculate the single-phase velocity of siphon flow. However, an intensive cavitation phenomenon occurs in the high-lift siphon hose and then a two-phase flow is formed. Research on the velocity of high-lift siphon flow is a prerequisite for the application of siphon drainage with a 4-mm siphon hose. Few investigations of this subject have been carried out. Hence, experiments on the high-lift （8 m〈H0〈10.3 m） siphon drainage in a 4-mm siphon hose were performed. The characteristics of siphon flow under different conditions were ob- served and test data were obtained. Comparisons between test results and calculated results showed that significant errors were given by the hydraulics formula. It is demonstrated that the effect of gas in a siphon hose should be included in the calculation of flow velocity. The findings can be used to determine the number of siphon hoses and layout of siphon drainage holes, and provide valuable information for geotechnical companies.

Aerodynamic optimization of a high-lift system with adaptive dropped hinge flap

The Adaptive Dropped Hinge Flap(ADHF) is a novel trailing edge high-lift device characterized by the integration of downward deflection spoiler and simple hinge flap, with excellent aerodynamic and mechanism performance. In this paper, aerodynamic optimization design of an ADHF high-lift system is conducted considering the mechanism performance. Shape and settings of both takeoff and landing configurations are optimized and analyzed, with considering the kinematic constraints of ADHF mechanism, and the desired optimization results were obtained after optimization. Sensitivity analysis proves the robustness of the optimal design. Comparison shows that the ADHF design has better comprehensive performance of both mechanism and aerodynamics than the conventional Fowler flap and simple hinge flap design.

民用飞机高升力系统扭矩限制器触发特性分析

扭矩限制器是民用飞机高升力系统中重要的过载保护装置,能够在触发后阻止过量的载荷沿传动线系传递。触发特性的研究对于扭矩限制器的设计有重要的意义。设计了一种滚子-摩擦片式的扭矩限制器,提出了一种球窝结构的建模方法,建立了动力学有限元仿真模型,研究了扭矩加载速率、动静摩擦片初始安装距离、预加碟簧力和球与球窝摩擦系数对触发特性的影响。研究结果表明,扭矩加载速率改变会影响触发时间但不改变触发扭矩值。相同初始安装距离时,触发扭矩分别与碟簧力和摩擦系数呈线性关系。研究为高升力系统的设计提供了参考。

高空升降框架的结构优化与有限元分析

沙漠环境中易出现的极端风载对设备的安全性能提出极高要求,现有高空升降框架的设计主要依靠工程经验,存在用料多、自重大、安全余量高等不足。针对此,采用CREO软件建立高空升降框架的三维实体模型,根据国标规定将风载等效为静载荷,采用ANSYS软件对极端风载作用下高空升降框架力学特性进行仿真计算。结果表明:系统与风载不存在共振风险,极限风载作用下系统最大应力幅值为166 MPa。进一步提出设计精细、造价经济的高空升降框架优化设计方案,在极限风载作用下,优化框架静力学计算结果表明:优化后系统的最大应力幅值在降低约35%的同时,可实现整体减重约17%。

非对称升力翼对高速列车横风气动性能的影响

随着高速列车运行速度的不断提升,横风环境下列车运行安全问题日益凸显。为此,从控制气动升力角度提出一种非对称升力翼结构以期形成抗倾覆力矩,并采用数值模拟方法,对比分析原始车型、全展开升力翼车型和收缩迎风侧升力翼车型的气动载荷及列车周围流场结构,探究横风环境下该结构对列车横风气动性能的影响。研究结果表明:升力翼对高速列车气动载荷及周围流场影响显著;列车安装升力翼后主要改变了车顶和车体背风侧表面压力分布以及车顶、车体背风侧和尾流区域的速度分布;车体顶部由于受到非对称升力翼压力面影响,在升力翼下方车顶区域形成了低速高压区且向车体背风侧延伸;同时,车体背风侧表面压力升高,在升力翼下游车体背风侧空间区域,由流动分离导致的漩涡结构发生了明显改变;相比于原始车型,收缩迎风侧升力翼车型(模型Ⅱ和模型Ⅲ)均可减小列车横向力和倾覆力矩;模型Ⅲ效果最显著,3车编组列车横向力和倾覆力矩分别减少13.19%和11.86%。

环状悬挑钢结构整体提升过程中局部失效研究

以北疆明珠塔旋转餐厅提升为例,通过有限元分析软件ABAQUS构建北疆明珠塔有限元模型,利用“生死单元”技术模拟不同位置构件失效,分析不同形式的局部构件失效对提升过程中旋转餐厅受力性能的影响规律,并通过现场实测数据验证了有限元模型的可靠性。结果表明:吊点处附近构件单独失效对结构应力和位移影响较大。且构件被完全提起前,构件失效越晚,构件失效前应力越大,结构动力响应越明显;此外,不同种构件同时失效对结构的影响大于单根构件失效影响的叠加,不相连同种构件同时失效对结构的影响大于相连同种构件同时失效,且影响程度随着失效构件之间距离的增加而减小。