1.
DELAYED RANS/LES Method For High Attack Angle Flow over Multi-element Airfoil
多段翼型大迎角分离流动的DELAYED RANS/LES混合算法
2.
NUMERICAL STUDY ON THE SLENDER BODY AT HIGH ANGLE OF ATTACK
细长旋成体大迎角分离控制数值研究
3.
Optimization of the large cone angle parameters of downhole oil/water separation hydrocyclone
井下油水分离旋流器大锥角参数优化
4.
Small diameter and little awl corner hydrocyclone has better separate, lower work capacity, large pressure drop and diffluence ratio.
小直径小锥角水力旋流器分离粒度小、处理量小、压降大、分流比大;
5.
NUMERICAL SIMULATION OF SUPERSONIC SEPARATED FLOW OVER BLUNT CONES AT HIGH ANGLES OF ATTACK
钝锥大攻角超声速分离流场的数值模拟
6.
Capturing Details of Secondary Separation and Successfully Simulating Strongly Unsteady Turbulence Flow in Vortex Breakdown Region
基于层流假设的三角翼大迎角绕流特性数值模拟研究
7.
Experimental investigation on pressure distribution characteristics of wings of ×× missile at supersonic speeds and high angles of attack
××导弹翼面超声速大迎角压力分布特性试验研究
8.
Nonlinear Dynamic Characteristics Analysis and Control of Aircraft at High-Angle-of-Attack;
飞机大迎角非线性动力学特性分析与控制
9.
NUMERICAL SIMULATION AND ANALYSIS FOR HYPERSONIC FLOW WITH SEPARATION OVER BLUNT CONE AT ANGLE OF ATTACK
钝锥有攻角分离流动的数值模拟及其分析
10.
A Discourse Analysis of American University President Welcome Messages on the Webpages-Viewed from the Perspective of Systemic-Functional Grammar
系统功能视角下美国大学网页中校长欢迎致辞的语篇分析
11.
flow separation region
水流分离区气流分离区
12.
This attitude helps to generate greater lift and reduce the distance needed for takeoff or landing.
合适的大迎角，有利于在较低的速度下产生足够的升力，以便于减少起飞滑跑距离。
13.
Numerical Investigation on the Unsteady Separation Flows Around Double-Delta Wings
双三角翼非定常分离流动的数值模拟研究
14.
Visualization and measurement study of vortex flow over delta wing with dorsal fins
带背鳍平板三角翼分离涡流场的显示与测量
15.
Influence of free surface to the flow separation of an airfoil with a small angle of attack
自由表面对小攻角翼型流动分离特性的影响
16.
Separation of Active Anthraquinone Ingredient in Chinese Rhubarb By High-Speed Countercurrent Chromatography;
利用高速逆流色谱分离大黄活性成分
17.
Computational and experimental investigation of plasma aerodynamic actuation based corner flow separation control in a compressor cascade
等离子体气动激励抑制压气机叶栅角区流动分离的仿真与实验
18.
The velocity distributions previously shown were for a single angle of attack.
先前的速度分布列分别为单一迎角.