Study of superlow speed aerofoil lift-drag force characteristic test;
超低速翼型升阻特性实验研究
NiAl alloyed aerofoil had been tested about cavitation damage in contraction-diffuser cavitation abrasion experimental water tunnel, the upper surface of cavitation damage aerofoil had been observed with SEM.
在收缩-扩散型空蚀磨损试验水洞中对NiAl合金翼型进行空蚀破坏试验,使用扫描电镜(SEM)对受空蚀破坏的翼型上表面进行了观测,结果表明翼型上表面有大量的空蚀针孔出现,并随着试验时间的不断延长而扩展成空蚀坑,蚀坑内有微裂纹出现,蚀坑间也出现了微裂纹,从而导致蚀坑的扩展和表面材料的去除。
At first, 5 kinds of different position of aerofoil maximum thickness belong to NACA0010 aerofoil are used to model pump through GAMBIT, the flow field inside axial flow pump is simulated by FLUENT, by comparing the volume of air bubble of pumps it can be known that the performance of anti-cavitation is the best when the maximum thickness of aerofoil at 50% of chord.
先对NACA0010系列的5种最大相对厚度位置不同的翼型分别在GAMBIT中进行轴流泵建模,通过FLUENT软件对5个泵内部流场进行三维数值计算,通过对比分析得出,翼型最大相对厚度在弦长的50%处时对汽蚀的抑制效果最好。
Numerical simulation on aerodynamic performance of an airfoil for wind turbine;
风力机叶片翼型气动特性数值模拟
Numerical simulation on airfoil stall separation suppression by plasma aerodynamic actuation;
等离子体气动激励抑制翼型失速分离的仿真研究
Numerical investigation of dynamic stall control using variable droop leading edge airfoil;
翼型动态失速的变下垂前缘控制数值模拟
Computation of Unsteady Pressure Distribution on a Profile in Transonic Flow;
二元翼型跨音速非定常压力计算
The influences of blade laying angle,solidity, blade shape,profile,blade relative thickness and impeller/hub ratio on the characters of impeller are calculated.
从搅拌桨的力与力矩平衡这两个基本方程出发，推导出轴流桨功率准数、流量准数与搅拌釜内能耗分配的理论计算式，并计算了桨叶的叶片安放角、盘面比、叶片形状、翼型、叶片的相对厚度、轮毂比对桨叶性能的影响。
The flow fields around a profile at a large attack angle with/without oscillating/steady excitation at the profile s leading edge have been numerical simulated.
本文数值模拟了施加振荡射流以及相应定常吸气条件下的翼型分离流动。
Compared t o the other airfoils used in reversible fan design, the combined cascades are co nsidered to be super to th.
与现有的翼型相比 ,CN +Rymax 、αN +RCymax均有不同程度的提
Design research of high lift, mild stall airfoils (BUAA K1/BUAA K2) was conducted in order to investigate their design strategy, methods and technology for a long endurance aircraft.
为了探索适用于长航时飞行器的翼型设计思想、方法和技术 ,进行了新型高升力及失速特性缓和的BUAA K1 BUAA K2翼型的设计研究 。
An embedded H grid technique is employed for generating grids of isolated airfoils and cascades.
提出一种嵌入式 H型网格技术 ,用于生成孤立翼型和叶栅的计算网格。
The model is based on the damage micromechanics and on wing crack nucleation and growth under dynamic compression.
运用细观损伤力学理论,从动态压缩载荷下陶瓷材料内翼型裂纹的产生和扩展的损伤机理出发,建立了陶瓷材料的弹脆性动态损伤本构模型,给出相应的损伤演化方程。