共查询到19条相似文献,搜索用时 78 毫秒
1.
《应用力学学报》2019,(5)
直接数值计算方法对航空飞行器机体气动噪声产生机理研究及噪声预测非常关键。本文基于在格子玻尔兹曼方法(LatticeBoltzmannMethod,LBM)框架下的大涡模拟方法(LargeEddy Simulation, LES)对SD-7003仿生翼型在较低马赫数条件下的气动噪声进行了直接数值计算,雷诺数选取为8.0×10~5。LBM方法采用多松弛时间近似,格子离散速度模型为D2Q9模型,LES方法的亚格子模型是动态Smagorinsky模型。噪声直接计算结果表明:LBM-LES方法能较精确地预测低马赫数及中低雷诺数条件下翼型气动噪声远场的声压,与实验结果相比,误差在10%以内;同时可以直接得到噪声声场及传播过程,并能揭示噪声的生成机理。 相似文献
2.
采用大涡模拟(LES)和声比拟(AA)结合的方法,在低马赫数条件下,对SD7003多孔翼型自噪声声场进行计算,研究多孔材料在不同来流迎角下对翼型自噪声远场声压的影响规律,并阐述噪声的影响机理。结果表明:LES与AA相结合的方法能够较为准确地计算多孔翼型的边界层特征以及远场声压,且数值模拟结果与实验结果非常吻合。来流迎角为0°时,多孔翼型整体声压级随着渗透率的减小先减小后增大,渗透率为5×10-11 m2时多孔材料的降噪效果最佳。多孔翼型整体声压级随着迎角的增大而增大,但多孔材料的降噪效果随着迎角的增大而减小。多孔材料的存在能够有效地削弱翼型表面的大尺度相干结构,使得翼型表面的RMS压强脉动峰值减小,从而抑制翼型远场噪声。 相似文献
3.
基于低雷诺数串置翼型气动特性研究 总被引:2,自引:0,他引:2
基于低雷诺数,应用二维CFD方法,对串置翼型的气动特性进行了数值模拟。比较了串置翼型布局与常规单独翼型的升阻特性。分析了翼差角度对串置翼升阻特性的影响,并且在保持鸭翼±5°偏角不变的同时,研究了两翼之间的距离以及安装的相对高度对整个串置翼型升阻特性的影响。发现上鸭翼与主翼相结合具有相对较高的最大升力系数和临界迎角, 可以显著改善串置翼型的气动特性。 相似文献
4.
5.
翼型空化绕流数值研究 总被引:2,自引:0,他引:2
空化是发生在流体机械上的复杂过程,理论研究遇到很大困难。本文引入合适的空化数值模型,将空腔界面近似为自由面,用界面构造精度较高的流体体积方法求解空腔位置,通过直接求解原始变量的NavuerStokes方程,数值模拟了无界域中空化在翼型上发生、发展和脱落的周期过程;并分析了空化产生对翼型表面的压力分布、翼型收到的阻力和升力的影响。结果表明,空化出现在翼型上表面;由于空化的产生,翼型表面压力分布不稳定,导致升力、阻力和流场压力出现波动,这是实际中产生噪声和损失的主要原因。 相似文献
6.
7.
蜻蜓翅膀具有独特的褶皱状形貌.研究者们致力于利用仿生学原理,设计在低雷诺数条件下具有更优气动性能的褶皱翼型.本文采用计算流体力学方法,求解二维不可压Navier-Stokes方程组,探讨了四种翼型(平板翼型、流线翼型、小幅度褶皱翼型和大幅度褶皱翼型)的气动表现.在低雷诺数条件下得到以下结果:(1) 较小幅度的褶皱结构有利于增加升力和减小阻力.(2) 雷诺数变化时褶皱翼型的升力系数呈非线性变化;在特定雷诺数区间,幅度相近的褶皱翼型会发生相对气动优势的转变.(3) 褶皱结构内的回流区通过减小粘性阻力,使得翼型总阻力下降.(4) 翼型前缘的极小区域会产生脉冲高升力,对升力表现产生较大影响.这些结果表明,调整褶皱幅度是实现褶皱翼型气动优化的有效方案. 相似文献
8.
基于涡流发生器的翼型失速流动控制及雷诺数效应影响研究 总被引:1,自引:0,他引:1
针对所设计的三角形涡流发生器开展用于翼型失速流动控制的风洞实验研究,重点讨论涡流发生器几何参数、方向角、安装位置及实验雷诺数等因素对翼型失速流动控制的影响。实验结果表明:涡流发生器作用下,在干净翼失速迎角后能够形成一个升力几乎不随迎角变化的相对稳定的高升力状态,抑制了失速流动的发生,与此同时阻力大幅下降;本文所设计的涡流发生器方向角过大时会削弱翼型失速流动控制的效果;同一涡流发生器作用下雷诺数过大其失速流动控制效果会急剧恶化,第一种涡流发生器控制翼型失速的雷诺数有效范围略宽于第二种涡流发生器。 相似文献
9.
空化和空蚀是影响水力机械能否安全、经济运行的主要因素之一.为了研究新的翼型结构——多孔翼型对于水力机械的空化及空蚀现象的影响,利用PROE建立具有不同微孔数的翼型模型,再借助Fluent软件对多孔翼型的三维绕流流场进行了定常数值模拟计算.基于伯努利定律,对具有不同孔数的翼型绕流流场进行流态分析.根据模拟结果显示的不同翼型结构的速度场和压力场的分布特征,从能量转换的角度出发,揭示了多孔翼型绕流流场的内在特性,即绕流翼型的流场(速度场、压力场)是随着孔数而变化的.结合空化发生的条件,说明采用多孔翼型结构对改善水力机械内部空化现象是有一定的作用的,通过数值模拟方法来分析研究水力机械内部的空化空蚀现象,可以作为实验与理论分析的参考.从一个新的角度,为改善水力机械的空化和空蚀现象提供了新思路. 相似文献
10.
利用同位非结构化网格上的压力加权修正算法 ,对翼型湍流绕流进行了数值分析。详细地给出了一孤立翼型在不同攻角下的分离流结构及翼型表面压力分布 ,为了显示非结构化网格方法在求解多连通流动区域的优越性 ,对双翼型绕流进行了数值计算。在数值分析中 ,对阵面推进法进行改进来生成三角形网格 ,采用有限控制体方法直接在物理空间中的非结构化网格单元上离散 Navier- Stokes方程及 k- ε方程 ,形成的代数方程组通过预条件矩阵共轭梯度平方法求解。计算结果表明 :当流动为附着流时 ,计算结果与实验值吻合程度令人相当满意 ;而在分离区内 ,计算结果与实验值存在一定的误差 ,需对分离区内的湍流模型做进一步的改进。 相似文献
11.
A study on the mechanism of high-lift generation by an airfoil in unsteady motion at low reynolds number 总被引:3,自引:0,他引:3
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
, 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.
The project supported by the National Natural Science Foundation of China (19725210) 相似文献
12.
Airfoil self-noise is a common phenomenon for many engineering applications. Aiming to study the underlying mechanism of airfoil self-noise at low Mach number and moderate Reynolds number flow, a numerical investigation is presented on noise generation by flow past NACA0018 airfoil. Based on a high-order accurate numerical method, both the near-field hydrodynamics and the far-field acoustics are computed simultaneously by performing direct numerical simulation. The mean flow properties agree well with the experimental measurements. The characteristics of aerodynamic noise are investigated at various angles of attack. The obtained results show that inclining the airfoil could enlarge turbulent intensity and produce larger scale of vortices. The sound radiation is mainly towards the upper and lower directions of the airfoil surface. At higher angle of attack, the tonal noise tends to disappear and the noise spectrum displays broad-band features. 相似文献
13.
The flow field of a flapping airfoil in Low Reynolds Number (LRN) flow regime is associated with complex nonlinear vortex shedding and viscous phenomena. The respective fluid dynamics of such a flow is investigated here through Computational Fluid Dynamics (CFD) based on the Finite Volume Method (FVM). The governing equations are the unsteady, incompressible two-dimensional Navier-Stokes (N-S) equations. The airfoil is a thin ellipsoidal geometry performing a modified figure-of-eight-like flapping pattern. The flow field and vortical patterns around the airfoil are examined in detail, and the effects of several unsteady flow and system parameters on the flow characteristics are explored. The investigated parameters are the amplitude of pitching oscillations, phase angle between pitching and plunging motions, mean angle of attack, Reynolds number (Re), Strouhal number (St) based on the translational amplitudes of oscillations, and the pitching axis location (x/c). It is shown that these parameters change the instantaneous force coefficients quantitatively and qualitatively. It is also observed that the strength, interaction, and convection of the vortical structures surrounding the airfoil are significantly affected by the variations of these parameters. 相似文献
14.
为改善小型风力机随机湍流工况适应性,以NACA0012翼型为研究对象,采用非嵌入式概率配置点法,获得随机湍流工况下小型风力机叶片翼型运行攻角分布规律;在气动优化中耦合层流分离预测,基于Transition SST模型、拉丁超立方试验设计、Kriging模型和带精英策略非支配排序遗传算法NSGA-II进行高湍流低雷诺数风力机翼型气动优化。结果表明,优化翼型叶片平均风能捕获效率分别提高3.01%和4.76%,标准差分别降低4.76%和14.93%,优化翼型湍流适应性增强。该方法将翼型设计与湍流风况相匹配,为湍流工况低雷诺数翼型及小型风力机设计提供参考。 相似文献
15.
Dong Li 《国际流体数值方法杂志》2007,54(3):325-332
The detached‐Eddy simulation (DES) method was applied to calculate pre‐ and post‐stall aerodynamic characteristics of airfoil stall. A discrepancy between numerical and experimental data was observed near the stall regime for the airfoil NACA64A‐ 006 which is a thin airfoil stall type. The reason of this discrepancy and one possible way for improvement of the numerical model are discussed here. It is shown that the use of the Baldwin–Lomax model in the RANS region improves the DES results in this case. If the relevant factors (grid density, time step, turbulence model, etc.) are appropriately taken into account, the DES approach could reliably predict stall aerodynamical characteristics. Copyright © 2006 John Wiley & Sons, Ltd. 相似文献
16.
D. N. Gorelov 《Journal of Applied Mechanics and Technical Physics》2008,49(3):437-441
Simple formulas for calculating the pressure and the total hydrodynamic reactions acting on an arbitrarily moving airfoil
are derived within the framework of the model of plane unsteady motion of an ideal incompressible fluid. Several vortex wakes
may be shed from the airfoil owing to changes in velocity circulation around the airfoil contour. Cases with nonclosed and
closed contours are considered.
__________
Translated from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 49, No. 3, pp. 109–113, May–June, 2008. 相似文献
17.
对称翼型低雷诺数小攻角升力系数非线性现象研究 总被引:12,自引:0,他引:12
采用Rogers发展的三阶Roe格式,求解非定常不可压N-S方程,时间方向为二阶精度双时间步方法, 数值模拟了对称翼型SD8020低雷诺数(Re=40000,100000)条件下,流场层流分离涡结构和升力系数随攻角的变化.同试验比较证明了数值模拟的正确性.通过对数值模拟时均化流场结果的详细分析,发现对称翼型在小雷诺数0°攻角附近出现的层流分离泡,其内部结构和演化规律都不同于经典层流分离泡模型,从而提出了一种后缘层流分离泡模型.并应用该模型对对称翼型小攻角低雷诺数流场特性以及升力系数非线性效应的形成机理进行了研究和解释. 相似文献
18.
Liang-Hsia Tsai Chien-Cheng Chang Roland Glowinski 《International Journal of Computational Fluid Dynamics》2018,32(2-3):158-166
ABSTRACTIn this article, we investigate the abnormal settling of two-disk systems and elliptical shaped particles in infinite two-dimensional channels filled with an incompressible viscous fluid. We apply a distributed Lagrange multiplier/fictitious domain method (DLM/FDM) for the direct numerical simulation of these particulate flows. Due to the wall effect, the two-disk systems can form chains which settle stably instead of having the particles moving apart. Also, sedimentation with the long axis moving to vertical positions in the middle of the infinite channel has been observed for the elliptic shaped particles. The critical Reynolds number for having such an abnormal settling behaviour decreases as the width of the channel increases. 相似文献
19.
等速上仰翼型动态失速现象研究 总被引:9,自引:0,他引:9
翼型大迎角绕流的静态失速将造成升力突降和气动性能急剧恶化,但利用非定常运动所产生
的动态失速效应,可以大大地延缓气流分离和失速现象的发生. 采用Rogers发
展的双时间步Roe格式,求解拟压缩性修正不可压N-S方程. 数值模拟了低雷诺数
($Re=4.8 \times 10^{4}$)条件下NACA0015翼型作等速上仰($\alpha
=0^{\circ} \sim 60^{\circ}$)的动态失速过程,同Walker的试验结果比
较,验证了计算结果的正确性. 研究了该过程中主涡、二次涡和三次涡的发展,升
力系数随攻角变化,以及不同上仰速度对动态失速效应所造成的影响. 相似文献