Effect of ambient wind on pressure wave generated by high-speed train entering a tunnel

Using three-dimensional, unsteady N-S equations and k-ε turbulence model, the effect of ambient wind on the pressure wave generated by a high-speed train entering a tunnel was studied via numerical simulation. Pressure changes of the train surface and tunnel wall were obtained as well as the flow field around the train. Results show that when the train runs downwind, the pressure change is smaller than that generated when there is no wind. When the train runs upwind, the pressure change is larger. The pressure change is more sensitive in the upwind condition than in the downwind condition. Compared with no wind condition, when the wind velocity is 10 m/s and 30 m/s, the pressure amplitude on the train head is reduced by 2.8% and 10.5%, respectively. The wall pressure amplitude at 400 m away from the tunnel entrance is reduced by 2.4% and 13.5%, respectively. When the wind velocity is-10 m/s and-30 m/s, the pressure amplitude on the train head increases by 3.0% and 17.7%, respectively. The wall pressure amplitude at 400 m away from the tunnel entrance increases by 3.6% and 18.6%, respectively. The pressure waveform slightly changes under ambient wind due to the influence of ambient wind on the pressure wave propagation speed.

An Investigation into the Effects of the Reynolds Number on High-Speed Trains Using a Low Temperature Wind Tunnel Test Facility

A series of tests have been conducted using a Cryogenic Wind Tunnel to study the effect of Reynolds number(Re)on the aerodynamic force and surface pressure experienced by a high speed train.The test Reynolds number has been varied from 1 million to 10 million,which is the highest Reynolds number a wind tunnel has ever achieved for a train test.According to our results,the drag coefficient of the leading car decreases with higher Reynolds number for yaw angles up to 30º.The drag force coefficient drops about 0.06 when Re is raised from 1 million to 10 million.The side force is caused by the high pressure at the windward side and the low pressure generated by the vortex at the lee side.Both pressure distributions are not appreciably affected by Reynolds number changes at yaw angles up to 30°.The lift force coefficient increases with higher Re,though the change is small.At a yaw angle of zero the down force coefficient is reduced by a scale factor of about 0.03 when the Reynolds number is raised over the considered range.At higher yaw angles the lift force coefficient is reduced about 0.1.Similar to the side force coefficient,the rolling moment coefficient does not change much with Re.The magnitude of the pitching moment coefficient increases with higher Re.This indicates that the load on the front bogie is higher at higher Reynolds numbers.The yawing moment coefficient increases with Re.This effect is more evident at higher yaw angles.The yawing moment coefficient increases by about 6%when Re is raised from 1 million to 10 million.The influence of Re on the rolling moment coefficient around the leeward rail is relatively smaller.It increases by about 2%over the considered range of Re.

The influence of the leading-edge angle of subgrade on the aerodynamic loads of a high-speed train in a wind tunnel

The purpose of this study is to establish the correlation between the boundary layer over the subgrade and the aerodynamic loads act-ing on the train model in conventional wind tunnel tests.Firstly,flow characteristics around the subgrade with different leading-edge angles(15°,30°and 45°)are investigated through the particle image velocimetry(PIV)experimental test method.Then,wind tunnel tests of the aerodynamic performance of a high-speed train are carried out.The results are compared with previous experimental data obtained by moving model tests.Results show that,due to the presence of a boundary layer,the pressure acting on the lower part of the train head decreases,while other locations are not significantly affected.This is the reason for the reduction of the aerodynamic drag and lift on the train.In addition,the reduction effects become more obvious when the thickness of the boundary layer increases.The experimental results obtained could serve as a calibration of aerodynamic forces for wind tunnel tests on high-speed trains.

Numerical Investigation of the Effects of Wind Tunnel Model Vibrations on the Measured Aerodynamic Properties of Airfoils and Wings

This paper presents a numerical prediction of the unsteady flow field around oscillating airfoils at high angles of attack by solving unsteady Reynolds-averaged Navier-Stokes equations with SST turbulence model in order to simulate the effects of wind tunnel model vibrations on the aerodynamic properties of airfoils,especially high-aspect-ratio wings in a wind tunnel.The effects of the phase lagging between different modes of oscillations,i.e.,the airfoil plunging oscillation mode,the pitching oscillation mode,and the forward-backward oscillation mode,are also studied.It is shown that the vibrations (oscillations) of airfoils can cause the unsteady shedding of large-size separated vortex to precede the stationary stall incidence,hence lead to a stall onset at some earlier (lower) incidence than that in the steady sense.The different phase lagging has different effect on the flow field.When the pitching oscillation mode has small phase lagging behind the plunging oscillation mode,the effect of vibrations is large.Besides,if the amplitude of the oscillations is large enough,and the different modes of vibrations match or combine appropriately,the unsteady stall may occur 2° earlier in angle of attack than the case where airfoils keep stationary.

Wind tunnel test on the effect of metal net fences on sand flux in a Gobi Desert, China

The Lanzhou-Xinjiang High-speed Railway runs through an expansive windy area in a Gobi Desert, and sand-blocking fences were built to protect the railway from destruction by wind-blown sand. However, the shielding effect of the sand-blocking fence is below the expectation. In this study, effects of metal net fences with porosities of 0.5 and 0.7 were tested in a wind tunnel to determine the effectiveness of the employed two kinds of fences in reducing wind velocity and restraining wind-blown sand. Specifically, the horizontal wind velocities and sediment flux densities above the gravel surface were measured under different free-stream wind velocities for the following conditions： no fence at all, single fence with a porosity of 0.5, single fence with a porosity of 0.7, double fences with a porosity of 0.5, and double fences with a porosity of 0.7. Experimental results showed that the horizontal wind velocity was more significantly decreased by the fence with a porosity of 0.5, especially for the double fences. The horizontal wind velocity decreased approximately 65% at a distance of 3.25 m（i.e., 13 H, where H denotes the fence height） downwind the double fences, and no reverse flow or vortex was observed on the leeward side. The sediment flux density decreased exponentially with height above the gravel surface downwind in all tested fences. The reduction percentage of total sediment flux density was higher for the fence with a porosity of 0.5 than for the fence with a porosity of 0.7, especially for the double fences. Furthermore, the decreasing percentage of total sediment flux density decreased with increasing free-stream wind velocity. The results suggest that compared with metal net fence with a porosity of 0.7, the metal net fence with a porosity of 0.5 is more effective for controlling wind-blown sand in the expansive windy area where the Lanzhou-Xinjiang High-speed Railway runs through.

翼形表面流动激励载荷特征试验研究

为了研究水下航行体翼形表面流动激励载荷特征,采用柔性基底微型传感器阵列,建立风洞中翼形结构表面流动激励载荷测试方法。分析了翼形表面层流、转捩、湍流发展过程中激励力试验特征,试验结果表明:翼形表面经过层流、转捩、湍流发展过程,随着来流速度的增大,翼形表面转捩区位置逐渐前移直至完全湍流。提出了转捩点预报修正方法,修正后预报值与试验值偏差在10%以内,为水下航行体翼形流动激励力相关研究提供试验基础。

Design of a large-scale model for wind tunnel test of a multiadaptive flap concept

The design and application of morphing systems are ongoing issues compelling the aviation industry.The Clean Sky-program represents the most significant aeronautical research ever launched in Europe on advanced technologies for greening next-generation aircraft.The primary purpose of the program is to develop new concepts aimed at decreasing the effects of aviation on the environment,increasing reliability,and promoting eco-friendly mobility.These ambitions are pursued through research on enabling technologies fostering noise and gas emissions reduction,mainly by improving aircraft aerodynamic performances.Within the Clean Sky framework,a multimodal morphing flap device was designed based on tight industrial requirements and tailored for large civil aircraft applications.The flap is deployed in one unique setting,and its cross section is morphed differently in take-off and landing to get the necessary extra lift for the specific flight phase.Moreover,during the cruise,the tip of the flap is deflected for load control and induced drag reduction.Before manufacturing the first flap prototype,a high-speed(Ma=0.3),large-scale test campaign(geometric scale factor 1:3)was deemed necessary to validate the performance improvements brought by this novel system at the aircraft level.On the other hand,the geometrical scaling of the flap prototype was considered impracticable due to the unscalability of the embedded mechanisms and actuators for shape transition.Therefore,a new architecture was conceived for the flap model to comply with the scaled dimensions requirements,withstand the relevant loads expected during the wind tunnel tests and emulate the shape transition capabilities of the true-scale flap.Simplified strategies were developed to effectively morph the model during wind tunnel tests while ensuring the robustness of each morphed configuration and maintaining adequate stiffness levels to prevent undesirable deviations from the intended aerodynamic shapes.Additionally,a simplified design was conceived for the flap-wing interface,allowing for quick adjustments of the flap setting and enabling load transmission paths like those arising between the full-scale flap and the wing.The design process followed for the definition of this challenging wind tunnel model has been addressed in this work,covering the definition of the conceptual layout,the numerical evaluation of the most severe loads expected during the test,and the verification of the structural layout by means of advanced finite element analyses.

Experimental and numerical investigation of the influence of roughness and turbulence on LUT airfoil performance

Vertical-axis wind turbines(VAWTs)have been widely used in urban environments,which contain dust and experience strong turbulence.However,airfoils for VAWTs in urban environments have received considerably less research attention than those for horizontal-axis wind turbines(HAWTs).In this study,the sensitivity of a new VAWT airfoil developed at the Lanzhou University of Technology(LUT)to roughness was investigated via a wind tunnel experiment.The results show that the LUT airfoil is less sensitive to roughness at a roughness height of<0.35 mm.Moreover,the drag bucket of the LUT airfoil decreases with increasing roughness height.Furthermore,the loads on the LUT airfoil during dynamic stall were studied at different turbulence intensities using a numerical method at a tip-speed ratio of 2.Before the stall,the turbulence intensity did not considerably affect the normal or tangential force coefficients of the LUT airfoil.However,after the stall,the normal force coefficient varied obviously at low turbulence intensity.Moreover,as the turbulence intensity increased,the normal and tangential force coefficients decreased rapidly,particularly in the downwind region of the VAWT.

Experimental study of the boundary layer over an airfoil in plunging motion

This is an experimental study on the bound- ary layer over an airfoil under steady and unsteady conditions. It specifically deals with the effect of plunging oscil- lation on the laminar/turbulent characteristics of the bound- ary layer. The wind tunnel measurements involved surface- mounted hot-film sensors and boundary-layer rake. The ex- periments were conducted at Reynolds numbers of 0.42 x 106 to 0.84 X l06 and the reduced frequency was varied from 0.01 to 0.11. The results of the quasi-wall-shear stress as well as the boundary layer velocity profiles provided impor- tant information about the state of the boundary layer over the suction surface of the airfoil in both static and dynamic cases. For the static tests, boundary layer transition occurred through a laminar separation bubble. By increasing the an- gle of attack, disturbances and the transition location moved toward the leading edge. For the dynamic tests, earlier transi- tion occurred with increasing rather than decreasing effective angle of attack. The mean angle of attack and the oscillating parameters significantly affected the state of the boundary layer. By increasing the reduced frequency, the boundary layer transition was promoted to the upstroke portion of the equivalent angle of attack, but the quasi skin friction coeffi- cient was decreased.

Airfoil Roof in Buildings

In this paper an airfoil that is used on roofs was analyzed:Circular Arc Airfoil.The JavaFoil program for the calculation of aerodynamic parameters of the simulated wing airfoil and small AR(aspect ratio)was used.A wing roof scale model was constructed,and it was tested in the wind tunnel of the Laboratory of Environmental Fluid Dynamics,Universidad Nacional del Comahue.In the model,the AR was equal to 1.46.Thickness of the model was 32%.The tests were conducted at a Reynolds number of 1×10^(5).The curves of the lift coefficient versus angle of attack were obtained,and the pressure coefficient Cp was determined for each surface.The lift coefficients and the Cp values differ from the theoretical profile;this shows the importance of using the wind tunnel to obtain experimental data to achieve a good structural design.

直接测力俯仰振荡翼型动态气动性能研究

在西北工业大学NF-3低速风洞二元实验段开展翼型俯仰振荡运动动态气动性能深入研究。实验模型为展向三段式测力模型,测力仅在模型中段进行以减小风洞侧壁干扰的影响。实验中采集模型的转动瞬态迎角、计算模型中段的惯性力和惯性力矩、并从天平采集数据中扣除以修正模型惯性对结果的影响。结果表明,迎角超过正向或负向静态失速迎角是升力系数和俯仰力矩系数产生大的迟滞环的必要条件。随着振荡缩减频率增大,动态失速会推迟,升力系数迟滞环增大,阻力系数增大,最大迎角附近的俯仰力矩系数减小。在迎角小于静态失速迎角或超过不大的迎角范围,随着缩减频率的增大,翼型振荡运动俯仰力矩系数上行时减小,下行时增大。随着振荡振幅的增大,翼型振荡运动动态升力系数和俯仰力矩系数的迟滞环增大。随着平均迎角的增大,翼型迎角更多地进入正向失速区,升力系数迟滞环增大,俯仰力矩系数最小值变小。雷诺数对升力系数、阻力系数和俯仰力矩系数迟滞环无明显影响;但是,在翼型模型下行过程,随着雷诺数的增大,升力恢复提前,同时迟滞环随雷诺数增大而减小。

旋翼翼型动态风洞试验技术研究

旋翼翼型的设计优化及性能确定亟须建立并发展翼型动态风洞试验技术。通过动力学仿真与结构优化设计,基于FL–11低速风洞研制出旋翼翼型两自由度动态试验装置,可实现俯仰/沉浮单自由或两自由度耦合运动,最高振荡频率达到5 Hz;基于FL–20连续式跨声速风洞研制出旋翼翼型高频高速动态试验装置,最高振荡频率达到17 Hz,试验最高雷诺数为5×106,模拟参数包线满足真实直升机参数要求;基于FL–14低速风洞研制出大尺度旋翼翼型动态试验装置,翼型模型弦长为800 mm,试验最高雷诺数达到4×106。完善了旋翼翼型动态试验精准测试相关技术,并开展了验证性试验,试验数据规律合理、量值可靠,表明试验系统及相关测试技术具有较高的可靠性,可为旋翼翼型动态气动特性试验评估提供重要的设备平台和技术支撑。

低温痕量水条件下翼型表面结冰特性的数值模拟研究

相比于传统的风洞设备,低温风洞可以生成更高雷诺数的气流,而风洞降温过程中残留的痕量水蒸气可能会影响试验件气动参数的测量。痕量水结冰的热力学过程复杂,实验测试较为困难,其机理仍需深入研究。针对该问题,本文基于欧拉方法建立了空气⁃过冷水滴⁃冰晶多相流模型,仿真结果与文献中的实验数据吻合度较高,进一步采用该模型获得了低温风洞中水蒸气凝结液滴/冰晶撞击翼型的结冰过程,探究了气流中总的水含量、融化比、气流温度、压力、马赫数等参数对结冰过程的影响,并定量分析了结冰现象对翼型气动参数的影响,可为低温风洞的实际运行提供一定的理论参考。

经典跨声速翼型RAE2822数据分析

经典跨声速翼型RAE2822风洞试验数据长久以来被广泛用于CFD计算方法和软件的验证与确认,但是数据的正确使用或者说合理使用仍存在一些需要研究和注意的问题,包括计算网格、风洞试验数据修正、中弧线修正、翼型几何定义和建模,以及摩擦阻力系数和边界层速度剖面的原始定义等。在开展CFD研究之前,必须首先对计算方法进行验证,尤其是要先尽可能消除计算结果对计算网格的依赖性;经过对目前可开放使用的计算网格的不足之处进行分析,研制了一套高品质的计算网格并获得了预期的一阶网格收敛性;通过计算软件交叉验证,进一步确保所用计算软件的可信度。在将CFD计算结果与翼型风洞试验数据进行比对时,通常需要对马赫数和攻角进行修正,且如何修正是一个需要持续研究的问题;翼型中弧线修正是一种有效的方法,但需要考虑流动参数的影响。原始翼型几何构型采用有限离散点定义,计算网格生成过程中需要采用插值方法布置型面网格点,不同插值方法对于翼型前缘附近流动的数值模拟有细微影响。多数相关研究工作只比对压力分布;少数研究工作会比对摩擦阻力系数、边界层及尾迹速度剖面,但在比对时,需要注意原始风洞试验相关参数定义与CFD计算常用定义的区别。

高湍流度对翼型气动性能影响的试验研究

为分析湍流度对低雷诺数大型风力机翼型气动性能的影响,以大型风力机翼型NREL S810为研究对象,采用风洞试验法,系统研究了湍流度对翼型NREL S810气动性能的影响,获得了翼型的升力系数、阻力系数和表面压力分布特性。结果表明:湍流度的存在使得S810翼型的气动力特性发生改变,最大升力系数先升高后降低,在湍流度为4.6%时翼型的升力系数最高;随着湍流度的增大,发生了明显的失速延迟现象,失速攻角持续后移,且湍流度增加会使得失速下降曲线变得平缓。

雷诺数和湍流度综合影响下翼型气动性能试验研究

如何精确地预测风力机翼型的气动性能,是目前设计优良的风力机叶片需要解决的一个关键问题。以大型风力机专用翼型NREL S810为研究对象,采用风洞试验测压方法,分析了高、低雷诺数下,湍流度对翼型气动性能的影响特性。结果表明:随着来流湍流度的增大,翼型的升力系数和阻力系数均呈先增大后减小的变化趋势,当湍流度为4.6%时增加至最大,之后开始下降;当湍流度小于11%时,随着雷诺数的增加,升力系数、阻力系数均增加;当湍流度增大至11%以上后,随着雷诺数的增加,升力系数、阻力系数均减小;随着雷诺数的增加,最大升阻比先增大再减小,并且最大升阻比对应的攻角呈先前移再后移的趋势。

Rotor airfoil aerodynamic design method and wind tunnel test verification

Well-designed airfoil is very important for high-performance rotor.This paper developed an efficient multi-objective and multi-constraint optimization design system for rotor airfoils based on RANS analysis,and verified the performance of the optimized airfoil.Using CRA09-A as the baseline rotor airfoil,the CRA09-B optimized rotor airfoil was designed successfully.Combined with the foundation of high-precision rotor airfoil stationary test technology,the CRA09-B and CRA09-A rotor airfoils were tested in the S3 MA high-speed wind tunnel of ONERA.In order to correct the aerodynamic data,a single parameter linear wall pressure method is used to consider the tunnel effects.The results indicate that multi-objective and multi-constraint optimization design method developed in this study is reliable,and that CRA09-B optimized airfoil provides better stationary performance than CRA09-A airfoil in terms of maximum lift coefficient and lift-to-drag ratio.

吸气式直流低速风洞实验平台设计与应用

为了研究风力机叶片、翼型、建筑模型的空气动力学性能和流场特性,研究设计了一套吸气式直流低速风洞实验平台。该平台由电动机、变频器、整流装置、收缩段、实验段及扩散段等部分组成,采用热线风速仪、皮托管、麦克风分别对实验段流场和噪声进行了测定,结果表明:设计的平台流场性能稳定,实验段来流风速在1.5~40 m/s范围内连续可调,来流湍流强度小于0.7%,且气动噪声值在来流风速低于25 m/s时低于90 dB,满足流场品质要求。进一步开展了风力机尾流特性、低矮房屋风载特性、翼型气动特性实验,探讨风力机、低矮房屋和翼型表面风压分布的变化规律,该研究结果可以为风洞实验设计、流场特性和缩尺模型的气动性能研究提供参考。

吸气式二元翼型风洞的气动设计

翼型是机翼等气动部件的二维截面,对于机翼乃至飞行器全机的气动性能都有着重要影响,所以翼型研究是先进飞行器设计的基础和重点。翼型风洞是进行翼型实验的最适用风洞,在翼型研究中发挥着不可替代的作用,但由于其专用性,目前关于翼型风洞设计的公开成果并不多见。基于翼型实验的参数要求,综合运用空气动力学知识,确定了一种吸气式二元翼型风洞的气动设计方案。设计的翼型风洞包括动力段、扩压段、实验段、收缩段和稳定段等洞体,并配有阻尼网、蜂窝器等内部整流装置。经过计算和分析,结果表明此风洞具有结构紧凑、湍流度低、能量利用率高的优势,可以较好完成翼型实验,推动飞行器技术发展。

适用于风力机的新翼型气动性能的实验研究

对适用于风力机的新翼型FFA W3 211和FFA W3 360进行了风洞实验研究,得到了两种翼型在不同雷诺数下的气动性能及其在大攻角下的失速特性。实验结果与采用低雷诺数翼型分析和设计软件XFOIL的计算结果进行了比较,其最大升力系数对应攻角偏差小于1,在-10°～+18°范围内,升力系数的平均相对偏差为5 1%,两种结果的一致性很好。