本文还分析了前缘分离涡破裂前后的流动现象和旋涡横截面流线图谱的变化规律。
This paper also presents analysis of the flow features ahead and behind of the leading edge vortex breakdown and the topological features of section streamlines.
本文描述绕锐前缘平板高超声速流动的数值模拟结果。
The results of numerical simulation of the hypersonic flow around a plate with a sharp leading edge are presented.
根据计算结果重点对前缘气膜冷却复杂三维流动以及整个叶片的气膜冷却特性进行分析。
Analysis of simulation results emphasizes on the complex 3d flow due to cooling near leading edge and blade cooling characteristics.
用圆柱和放大的叶片做模型，模拟叶片前缘和叶盆凹面的流动。
Cylinder and enlarged blades are used as test models for simulating the leading edge and concave surface of the blade.
实验研究了矩形空腔在外部高速气流作用下诱导的空腔内流动振荡问题，以及从空腔前缘加入纯音声激励以抑制空腔内流动振荡的技术。
The flow induced oscillation in a cavity exposed to external high speed flow and its suppression by means of sound excitation at the leading edge of the cavity are experimentally studied.
该前缘部包括多个错开的孔以便使流体在该翼面部的表面上流动。
The leading edge portion includes a plurality of staggered holes for causing fluid to flow over a surface of the airfoil portion.
用实验方法研究了压气机叶片前缘分离流动结构。
The test model used in this study consists of circular leading edge and elliptic leading edge.
研究显示，前缘分离涡破裂后，流动的非定常脉动特性非常明显，这种非定常效应对机翼气动弹性特性的影响不可忽略。
It is shown that the unsteady fluctuation characteristics of the flow become highly obvious after the vortex breakdown, which exert a significant impact on the aeroelastic characteristics of the wing.
凸型间隙在叶片前缘引起了流动分离，凹型间隙存在一高速区，增加了二次流损失。
There are flow separations at the front blade of bulge tip clearance. The high speed area of groove tip clearance increases the secondary flow loss dramatically.
凸型间隙在叶片前缘引起了流动分离，凹型间隙存在一高速区，增加了二次流损失。
There are flow separations at the front blade of bulge tip clearance. The high speed area of groove tip clearance increases the secondary flow loss dramatically.
应用推荐