控制气泡逸出技术的计算研究

采用欧拉方法的混合两相流模型及标准k-ε湍流模型,对采用控制气泡逸出技术的高速艇进行数值模拟,得到模型在喷气与不喷气状态下航行时的粘性流场,探讨不同控制气泡逸出方法对摩擦阻力减阻效果的影响,以寻求出使气泡在艇底保持及运动稳定性较好的最佳减阻措施。计算结果表明:在艇底加防溅条没有达到预期的减阻效果,优化后的新船型明显提高微气泡的减阻率。     

超细长三体船阻力计算研究

主船体为超细长体,两侧配置两个小侧体而形成的三体船是一种很有潜力的新船型,近年来已引起了广泛的关注。本文对三体船的阻力原理进行了分析,以“相当平板”假设为基础计算摩擦阻力,采用“1＋k”的方法计算形状阻力;采用线性兴波阻力理论建立三体船的兴波阻力计算方法,提出了一套计算三体船阻力的完整方法。经与船模试验结果比较,采用本方法预报三体船的阻力,Cw的计算结果可以定性地反映侧体布置位置对三体船兴波阻力的影响,计算结果比较接近实际情况,具有一定的可靠性,可用于该船型的阻力预报。     

磁探搜潜系统的目标信号识别

文章主要介绍了磁探仪的系统结构和工作原理,重点介绍了磁探仪对磁目标信号的识别功能,以及对磁探仪未来发展的展望。     

双甲板拖网渔船导管桨的设计

针对某型双加甲板拖网渔船导管桨,建立基于底拖网作业渔船工况和自航工况的综合性船、机、桨优化匹配模型,对船机桨进行多重比较优化。采用导管和大直径螺旋桨,并通过生产实践,验证优化设计的高效性,提高拖网渔船推进系统的效率,增大系柱的拖力。     

Experimental study on microbubble ejection method for frictional drag reduction

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.     

The drag on an airplane taking off from a floating runway

The motions of an infinitely long, two-dimensional runway subjected to the dynamic moving load imposed by an airplane taking off are investigated. The runway is assumed to be floating in an inviscid fluid and is initially at equilibrium before the plane takes off. The deformation of the runway resulting from the take-off is wave-like and moves in the same direction as the plane. The maximum drag occurs when the plane catches up with the first wave. Three different runway configurations were considered: a baseline and ones which were ten and one hundred times more flexible than the baseline. For these runways, the added drag to the aircraft was very small, ranging from 1% for the stiffest to 10% for the most flexible runway.     

前扰流板对机舱进气量和车辆气动阻力的影响研究

为研究前扰流板高度变化对发动机舱进气量和整车风阻系数的影响,首先采用CFD软件对整车的基础模型进行气动性能仿真,并与实车风洞试验结果进行对比,确定仿真模型的计算精度;然后在该基础模型上添加不同高度的前扰流板进行仿真。结果显示,在前保险杠下方添加高度合适的前扰流板可有效降低整车风阻系数和提高冷却系统进气量。     

高密度中低速全垫升气垫船越峰问题的探讨与实践

1吨级试验艇属于高密度中低速气垫船,其与气垫密度成平方关系的阻力峰值较大而设计推力相对较小,经采取措施解决了越峰困难问题。原阻力计算方法在阻力峰值处的计算结果不够精确是原因之一,故根据移动压力面兴波理论编制了直接计算兴波阻力的程序,使计算越峰所需推力更接近试验结果。理论计算与工程实践表明,在设计高密度中低速气垫船时需特别关注越峰性能校核,建议第一阻力峰处设计越峰裕度在原计算方法基础上应修正至不小于30%为宜。     

动波壁圆柱流场的数值模拟与减阻机理

利用计算流体力学软件Fluent开展动波壁圆柱绕流的数值计算,建立二维运动波浪壁圆柱模型。在来流速度u=0.005 m/s、雷诺数Re=500的情况下,开展动波壁波动速度c=0,0.005,0.01,0.015,0.02,0.025,0.03,0.04 m/s等8个工况的计算分析,并比较不同波动速度对流场结构、升力、阻力特性的影响。结果表明:动波壁圆柱能有效抑制流动的分离,消除交替脱落的尾涡,减阻效果突出;随着波动速度的增大,平均阻力系数呈明显下降趋势;当波速超过0.025 m/s时,阻力变为负值,即波动圆柱产生一定的推力。