共查询到20条相似文献,搜索用时 0 毫秒
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本文借助Ansys Fluent开展平板仿生沟槽表面减阻性能数值模拟研究,系统分析沟槽形状、几何尺寸等参数对其减阻性能的影响。数值模拟结果表明,平板表面仿生沟槽的存在使得平板表面的剪应力大幅减小,且可以大幅降低平板表面的速度梯度,因而可以起到减阻的效果。另外,通过对比分析3种不同沟槽形状平板的减阻性能发现,V形沟槽的减阻性能较U形和L形减阻性能更优,在后续设计中可考虑V形沟槽。 相似文献
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基于OpenFOAM的平板微气泡减阻数值分析 总被引:2,自引:0,他引:2
《船舶力学》2020,(8)
本文基于OpenFOAM两相欧拉求解器(twoPhaseEulerFoam)对二维平板进行微气泡减阻数值模拟。模型直接求解两相N-S方程,同时采用标准k-ε湍流模型,并考虑两相间作用力的影响,通过求解界面输运方程来模拟气泡的聚并和破碎。将数值结果和Madavan[1]试验结果进行对比,验证了模型的可行性。分析了不同流速下气泡直径、通气速度、浮力对减阻率的影响,并且研究了气泡对边界处流体速度分布、气体体积分数的影响。从数值结果可以看出通气速度较大且气泡直径较小时,减阻效率高,并且浮力对减阻有一定影响。 相似文献
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风力机叶片翼型气动特性数值模拟 总被引:1,自引:0,他引:1
针对NACA63-215翼型绕流流动建立了二维可压缩湍流模型,利用商业软件NU-MECA进行了相应的数值模拟计算.湍流粘度分别采用基于RANS的Spalart-Allmaras和Baldwin-Lomax两种湍流模型来处理,得出了雷诺数为3×106时,翼型NACA63-215的升力系数和阻力系数随来流攻角的变化关系及压力分布图,并与试验数据进行对比.研究结果表明:Spalart-All-maras湍流模型比Baldwin-Lomax湍流模型在预测翼型失速后气动性能方面更加有效,Spalart-Allmaras湍流模型在大攻角下较易收敛且计算出的翼型气动性能与试验值更接近. 相似文献
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Hiroharu Kato Kento Miura Hajime Yamaguchi Masaru Miyanaga 《Journal of Marine Science and Technology》1998,3(3):122-129
The formation of air bubbles ejected through a single hole in a flat plate was observed in uniform flow of 2–10 m/s It was
confirmed that the size of the air bubbles was governed by main flow velocity and air flow rate. According to previous experiments,
the size of the bubbles is an important factor in frictional drag reduction by microbubble ejection. Usually bubbles larger
than a certain diameter (for example 1 mm) have no effect on frictional drag reduction. Three different methods were proposed
and tested to generate smaller bubbles. Among them, a 2D convex (half body of an NACA 64-021 section) with ejection holes
at the top was the best and most promising. The diameter of the bubbles became about one-third the size of the reference ejection
on a flat plate. Moreover, the bubble size did not increase with increasing flow rate. This is a favorable characteristic
for practical purposes. The skin friction force was measured directly with a miniature floating element transducer, and decreased
drastically by microbubble ejection from the top of the 2D convex shape. 相似文献
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A minimization theory, which is based on the Hilbert space theory, is proposed and applied to two-dimensional cavity flow
past a strut with the assumption of potential flow. That is, the minimization of the cavity drag of the strut on the cavity
flow is studied with the help of the optimization theory proposed. To accelerate the optimization process, the Euler beam
theory is introduced to generate a small variation in the strut. The introduction of the Euler beam theory makes the mathematical
formulation for the present theory ill-conditioned. To overcome this condition, the Tikhonov regularization and the Morozov's
discrepancy principle are used to regularize the present optimal theory. From the numerical study, it is shown that the proposed
minimization theory is able to find an optimized shape for the given strut and corresponding optimized cavity drag.
Received: June 22, 2000 / Accepted: January 30, 2001 相似文献
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应用CFD数值仿真预报方法,系统分析正弦前缘各参数对三维机翼气动性能的影响。应用分离涡模拟方法,绘制并比较标准和正弦前缘三维机翼的气动性能曲线,给出压力系数云图和流线分布云图。数值分析结果表明:当波高为3 mm、正弦前缘布置范围大于30%展长、正弦波周期为5.5时,与标准三维机翼相比,最大升力系数提高19.7%,失速角延迟16.7%。研究结果确定最佳的参数组合,有效抑制三维机翼大攻角工况下的失速现象。 相似文献
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襟翼舵作为一种可靠的、高升力的舵在最近几年内引起了广大设计工作者的重视影响,同时也有不少成熟的研究成果。对襟翼舵的研究主要集中在展弦比,主副舵面积比,转角比等方面,这些因素对襟翼舵的整体影响规律也已得到不少专家的解释。本文主要研究襟翼舵主副舵间间隙大小以及尺度效应对其水动力性能的影响,以普通NACA0020翼型为基本剖面建立不同间隙大小的襟翼舵模型,采用RANS方法计算得到了不同缝隙大小以及不同缩尺比下的襟翼舵升力阻力以及压力分布,并对周围涡结构以及流场进行分析,发现升力系数随着缝隙增大而减小,阻力系数先减小再增大的规律。同时随着襟翼舵尺度的增大,升力系数会随之增大,阻力系数会随之减小。文中以计算模型和实验数据进行对比,两者误差在5%以内,证明了计算结果的可靠性。 相似文献
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