前后缘改形翼型的流动控制机理研究

针对前后缘及上下表面正弦波浪型改形翼型对前缘流动分离及失速的影响,采用大涡模拟湍流模型对改形翼型在雷诺数1.6×105下不同攻角的流动控制机理进行了数值研究.研究表明,相对于NACA0012直翼型,改形翼型由于其前后缘及上下表面沿展向呈正弦波浪型变化的结构特性,使其在失速区得到了更平缓的升力曲线.在小攻角(α≤ 12°)工况,改形翼型的升力系数稍小,然而在大攻角(α≥15°)工况,其升力系数明显提高,最高可达20％.前后缘改形的扰流使得改形翼型前缘流动分离在最大截面处延迟了,分离线移至大约0.25c的位置,这样的三维流动结构有效的减少了升力在失速区的突降.     

海流能转换器叶片翼型的失速和水动力特性的数值研究

海流能转换器叶片翼型的水动力学性能优劣是海流能开发利用的关键因素.该文基于浙江工业大学水力学实验室设计的海流能转换器叶片,利用商川CFD模拟软件FLUENT对其叶片翼型在来流攻角从-4°～20°情形下的水动力特性进行了相应的数值模拟计算,得到翼型周围流场的速度分布、压力分布、翼型的失速特性以及水动力特性与攻角α的关系,可供设计高效的海流能转换器叶片时参考.     

变形振荡翼的动态失速特性研究

该文针对NACA0012振荡翼型动态失速流动现象,采用二维非定常数值模拟的方法,在考察湍流模型和网格分辨率影响的基础上,对比了动网格、多参考系动流域和网格点直接更新法模拟翼型动态失速引起气动力非线性迟滞特性的能力,并侧重分析了轻失速和深失速工况、刚性翼和圆弧变形翼的升阻力曲线及涡量场随攻角变化的演化过程。结果表明:(1)三种模拟振荡翼流场的数值计算方法是等价的;(2)轻失速和深失速工况下的流场结构区别明显,轻失速在振荡周期内流场结构变化不大,而深失速流场出现了明显的分离涡结构,变化剧烈;(3)不同大小变形量对翼型升力系数有着明显影响;合适的变形量大小能够减弱翼型下俯过程中的升力振荡现象;变形量的增大可抑制上仰过程中涡的分离,从而推迟了深失速迟滞效应的发生。     

垂直轴潮流能涡轮机水动特性研究

潮流能水轮机日益受到重视,针对其叶轮翼型水动力问题,提出了一种襟翼控制策略,计算不同襟翼翼型的垂直轴潮流能涡轮机水动力学动态特性,对比分析了襟翼控制前、后的垂直轴潮流能涡轮机力矩系数周期性变化规律。结果表明:所提控制策略可在不影响力矩系数均值的情况下,有效降低力矩系数振幅,且非对称襟翼翼型力矩系数振幅小于对称襟翼翼型;通过分析流场结构发现,施加控制策略的翼型尾缘流场较未施加控制策略的尾缘流场细长;襟翼控制叶片转过之后的尾涡贴合于旋转轨迹,对下游流场影响较小,易于耗散;发生大涡分离的方位角范围为160°~260°,叶片内侧涡强增大,而施加控制策略之后,该现象得到很好改善。     

水下循迹航行器水动力学性能数值研究

为了研究低速水下循迹监测航行器的水动力学性能数值计算问题,采用FLUENT软件和SST剪切应力输运模型,通过雷诺时均N-S方程分析流速一定的情况下,取不同攻角、不同水平舵角作为来流条件,研究未安装推进器以及安装推进器且其安装位置不同时,航行器的升力系数、俯仰力矩系数、表面压力分布和流场速度的变化规律。结果表明:在未安装推进器以及推进器的安装位置不同时,随着攻角的变化,升力系数呈线性变化,俯仰力矩系数呈非线性变化;随着水平舵角的变化,升力系数和俯仰力矩系数呈线性变化。当推进器安装在航行器头部时,对航行器流场压力和流场速度变化影响最大;当安装在航行器尾部时,对二者影响最小。对于低速航行器,应尽量将推进器安装在中间靠后位置,以提高航行器的水动力性能。升力系数的试验结果与数值仿真结果之间最大相差7. 51%,阻力系数的试验结果与数值仿真结果最大相差5. 84%,均吻合较好。研究结果可以为低速水下循迹航行器的优化设计和发展提供理论参考。     

振荡流下带圆角单柱体绕流特性数值研究

为研究带圆角柱体在非均匀流场中的水动力特性,基于流体动力学计算软件Fluent,运用层流模型对振荡流(Re=160,KC=7)下带圆角单柱体的绕流问题进行二维数值模拟研究,分析来流攻角和圆角半径两个参数对柱体尾涡结构和流体力系数的影响,并揭示其流体运动机理。研究发现:来流攻角和圆角半径的变化均会对柱体结构的流场特性和流场力系数影响显著;同时,不同来流攻角下,圆角半径的影响程度会发生改变。当α=0°与R⁺≤0.2时,升力系数时程曲线呈现拍频现象,且其FFT谱会存在主次频;此外,当来流攻角增大时,升力系数的脉动性会增强。当α≤22.5°时,惯性力系数起主导作用,而当α>22.5°时,拖曳力系数起主导作用。     

临界区雷诺数下翼型流场电磁力控制的脱体涡模拟

利用Maxwell方程直接数值计算表面包覆电极与磁极翼型产生的三维Lorentz力分布,将其加入到流体控制方程的动量方程中,采用脱体涡模拟方法对临界区雷诺数下受Lorentz力作用下翼型绕流场进行数值模拟,研究分析了电磁力作用系数和攻角对翼型绕流场结构及其升阻力系数的影响机理和规律。结果表明,Lorentz力可以有效地改善翼型周围的流场结构,达到减阻、增升、消涡以及延缓和抑制其失速的目的,因此是翼型的一种有效流动控制手段。     

水平轴水轮机叶片翼尾弯角对水动力性能的影响研究

为了研究水轮机叶片翼尾弯角变化对水动力性能的影响机理,使用翼型X-foil设计软件对NACA0014翼型进行弯角变形,得到上弯5°、10°和下弯5°、10°、15°五种变形翼型,并通过CFD仿真计算得到不同翼型的各个参数对比情况,最后进行了样机实验,验证所得结论的准确性。结果表明:下弯15°翼型升力增幅达到72%;翼尾下弯可使翼型上下表面压差显著增加,翼尾每下弯5°,压差可增加0. 25左右;随着下弯程度增加,流场出现分离现象,翼型失速临界攻角降低,更易失速;翼尾上弯使得变形翼型在升阻力和失速性方面均比原始翼型变差。该研究较清楚地揭示了叶片翼尾弯角对水轮机水动力性能的影响机理,为叶片设计与优化提供了翼型层面上的参考。     

桨叶剖面空泡形态发展特性研究

船后螺旋桨空泡诱导脉动压力与空泡形态发展特性密切相关。该文基于单一介质输运方程和Singhal全空泡模型,对NACA翼型进行了局部空泡流的数值计算,计算的平均压力分布和空泡长度与试验结果吻合较好。采用该方法针对Eppler方法设计的叶剖面的空泡形态发展进行了数值分析,提出了一种描述空泡形态几何参数(长度、体积)随新组合环境参数(攻角、空泡数、起始攻角及吸力面主压区压力系数)变化关系的统一表达式,并应用于描述平板空泡形态线性化理论结果、圆弧形水翼空泡形态试验结果以及Eppler方法设计的叶剖面空泡形态数值计算结果,并进行了理论说明。这为控制螺旋桨空泡行为,进而降低空泡脉动压力的螺旋桨设计奠定基础。     

自由表面对小攻角翼型流动分离特性的影响

该文介绍了在实验段为1.7m ×0.4m×0.4m的小型风浪槽中进行的自由表面附近,小攻角翼型流场分离特性的PIV实验结果.实验测量了NACA0012翼型在10°攻角下与自由表面多种不同间距时,翼面附近速度场,而后将各间距下连续采集的约500副瞬态流场结果进行统计分析,获得了翼面时均速度场等信息,讨论了时均流场结构和速度分布随翼型与水面间距的变化规律及水面对翼面流场分离特性的影响.实验的雷诺数Re=5.7′104.实验结果表明,随着翼型与自由表面间距的不同,翼型表面流动结构和气流在翼型表面的分离结构发生明显的变化,其明显的变化特征为,随着翼型从无水面干扰的工况向水面接近的过程中,上表面的分离先逐渐增强,而后被抑制,该流动演化特性进而可引起作用于翼型的气动特性的变化.     

Hydrodynamic performance of a vertical-axis tidal-current turbine with different preset angles of attack

The instantaneous angle of attack on the blade has a significant effect on the hydrodynamic performance of a vertical-axis tidal-current turbine with straight blades. This paper investigates the influence of different preset angles of attack on the hydro-dynamic performance of a three-bladed, vertical-axis, tidal-current turbine both experimentally and numerically. Experiments are carried out in a towing tank. This tested turbine’s solidity is 0.1146. The preset angles of attack on the blade are -3°, 0° , 3° , and 5°, in the experiments. Experimental results show that with the increase of the preset angle of attack from -3°, to 5° , the hydrodynamic performance of the turbine is improved significantly with the power coefficients being increased from 15.3% to 34.8%, respectively. Compared to the result of a 0° preset angle of attack, the performance of the turbine with positive preset angles of attack is experimentally demonstrated to be beneficial. This performance improvement is also shown by numerical     

Hydrodynamics of the interceptor on a 2-D flat plate by CFD and experiments

Nowadays, the use of interceptor by both partial and total dynamic lift crafts is quite common. In this article, a lot of evidence is given regarding the effectiveness of interceptor. The interceptor, when placed at the stern region, changes the pressure distribution around the craft. Its presence affects drag force, lifting force and the position of pressure's center leading to a new trim. This study focuses on hydrodynamic effects of interceptors on a 2-D flat plate based on both computational fluid dynamic(CFD) and experimental approaches. The Reynolds average Navier-Stokes(RANS) equations are used to model the flow around a fixed flat plate with an interceptor at different heights and attack angles. Based on finite volume method and SIMPLE algorithm which uses static structures, this model can be analyzed and the RANS results can be compared with the experimental data obtained in the current channel of the laboratory of waves and current of COPPE/UFRJ(LOC in Portuguese acronym). According to the results, the increase of pressure at the end of the flat plate was proportional to the interceptor height. In addition, the existence of interceptors can significantly increase the lift force coefficient at high angles of attack also proportional to the interceptor height. The presence of interceptor at the end of the flat plate increased both the lift coefficient and the drag coefficient but hydrodynamic drag did not grow as fast as the lift coefficient did. The lift coefficient increased much more. Furthermore, the results showed that the interceptor effectiveness is proportional to the boundary layer thickness at the end of the flat plate. As the interceptor was inside the boundary layer alterations of flow speed led to changes in boundary layer thickness, directly affecting interceptor's efficiency. Optimum choice of interceptor height had a great effect on its efficiency, and in choosing it the flow speed and length of the boat must be taken into consideration.     

Performance of the bio-inspired leading edge protuberances on a static wing and a pitching wing

It is shown that the leading edge protuberances on the flippers of a humpback whale can significantly improve the hydrodynamic performance. The present study numerically investigates the flow control mechanisms of the leading edge protuberances on a static wing and a pitching wing. For static wings, the performance in both laminar flow and turbulent flow are studied in the context of the flow control mechanisms. It is shown that the protuberances have slight effects on the performance of static wings in laminar flow. Also, it could be deduced that non-uniform downwash does not delay the stall occurrence in either laminar flow or turbulent flow. In turbulent flow, the leading edge protuberances act in a manner similar to vortex generators, enhancing the momentum exchange within the boundary layer. Streamwise vortices do contribute to the delay of the stall occurrence. The normal vorticity component also plays an important role in delaying the stall occurrence. However, for the pitching wing, the effect of leading edge protuberances is negligible in turbulent flow. Detailed analysis of the flow field indicates that for the wing with the leading edge protuberances, the leading edge vortices become more complex, while the thrust jet and the vortices in the wake are not changed significantly by the leading edge protuberances.     

PREDICTION OF HYDRODYNAMIC PERFORMANCE OF THE FLAP RUDDER

1.　INTRODUCTIONAs an unconventional type of rudder,the flap rudder can enhance the lift force,improve the hydrodynamic performance and delay the occurrence of separation comparedwith normal rudders.Therefore flap rudders have been used on ships in many cases.In1 968,Kato etal.did the experimental researches on flap rudder in open water[1 ] .In 1 992 ,Kose et al.carried out tests to study the hydrodynamic performance of flap rudder in openwater and behind a propeller[2 ] .The researches …     

NUMERICAL STUDY OF FLOW PAST AN AXISYMMETRIC BODY WITH A RING WING AT VARIOUS ATTACK ANGLES

1 .　INTRODUCTIONFortraditionalbody fittedgridsystemusedtocomputetheflow pasttheaxisymmetricbody ,thesingularityonthelongitudinalaxisisalongstand ingobstacle .Rationalsolutionishardtobeachievedevenwithfinemeshesgeneratedwithinthevicinityofthelongitudinalaxis .Hence ,appro priategridsystemisreguiredtoavoidthesingulari ty .Extensivenumericalexperimentsareconductedtoobtainthedesired gridsysteminthis paper .BasedontheideaofDDM[1] ,theoriginalflowfieldofthebodyisdividedinto 8sub domainsac cor…     

平板扰流片高度对壁面压力分布的影响

在风洞中研究了扰流片高度和底部间隙对平板扰流片引起的底板壁面压力分布的影响。用电子扫描阀测量的压力分布结果表明，底部没有间隙时，扰流片高度的增加不影响扰流片前后分离点、再附点以及主涡相对位置的变化；而下游回流区二次涡的相对高度随着扰流片高度的增加而增加，导致该区域无量纲压力系数绝对值减小。底部相对间隙在0.8～2.0之间时，扰流片高度小于边界层厚度时的壁面平均压力比扰流片高度大于边界层厚度时小30%左右。底部间隙对各种扰流片引起的壁面压力分布的影响趋势完全相似。     

新型叶剖面设计及叶剖面参数对空泡特性影响的研究--(1)新型叶剖面设计

本文是新型叶剖面设计及叶剖面参数时空泡特性影响的研究的第一部分：新型叶剖面设计。基于Eppler的机翼叶剖面设计理论给出了一种新的螺旋桨叶剖面设计方法。新的设计方法是利用预先给定拱度和厚度分布而不是攻角分布来设计叶剖面，从而在叶剖面的设计过程中可以控制叶剖面的最大厚度和拱度。这样，新的设计方法可以根据螺旋桨在各个半径上的最大厚度和拱度及水动力特性的要求设计各个半径上的叶剖面，为系统地研究叶剖面参数对其空泡特性的影响提供了一种有效工具，并为螺旋桨和叶剖面的同步优化设计打下基础。