首页> 外文OA文献 >Lift and Drag of Non-conventional Wings at Subsonic Speeds and Zero Angle of Attack - An Experimental Investigation

【2h】

Lift and Drag of Non-conventional Wings at Subsonic Speeds and Zero Angle of Attack - An Experimental Investigation

机译：以亚音速速度和零攻角升降和拖曳非传统翅膀 - 实验研究

代理获取

本网站仅为用户提供外文OA文献查询和代理获取服务，本网站没有原文。下单后我们将采用程序或人工为您竭诚获取高质量的原文，但由于OA文献来源多样且变更频繁，仍可能出现获取不到、文献不完整或与标题不符等情况，如果获取不到我们将提供退款服务。请知悉。

页面导航

著录项
引文网络
相似文献
相关主题

著录项

作者
Abdulkareem Shafiq Mahdi Al-Obaidi; Ting Chern Wei;
展开▼
作者单位

展开▼
年度 2018
总页数
原文格式 PDF
正文语种
中图分类

相似文献

外文文献
中文文献
专利

1. Lift and Drag of Non-conventional Wings at Subsonic Speeds and Zero Angle of Attack - An Experimental Investigation [J] . Abdulkareem Shafiq Mahdi Al-Obaidi, Ting Chern Wei MATEC Web of Conferences . 2018,第1期

机译：非常规机翼在亚音速和零迎角下的升起和阻力-实验研究
2. Experimental investigation into wing span and angle-of-attack effects on sub-scale race car wing/wheel interaction aerodynamics [J] . S. Diasinos, A. Gatto Experiments in Fluids . 2008,第3期

机译：机翼跨度和攻角对小尺度赛车机翼/车轮相互作用空气动力学影响的实验研究
3. Experimental investigation into wing span and angle-of-attack effects on sub-scale race car wing/wheel interaction aerodynamics [J] . Diasinos S, Gatto A Experiments in Fluids: Experimental Methods and Their Applications to Fluid Flow . 2008,第3期

机译：翼展和攻角对小型赛车翼/轮相互作用空气动力学影响的实验研究
4. Lift and Drag of Flapping Membrane Wings at High Angles of Attack [C] . Mohamed Y. Zakaria, David Allen, Craig A. Woolsey, AIAA applied aerodynamics conference;AIAA aviation forum . 2016

机译：拍击膜翼在高攻角下的起升和阻力
5. BASE DRAG EFFECTS ON MAXIMUM LIFT-TO-DRAG RATIO AIRFOILS AT MODERATE SUPERSONIC SPEEDS [D] . PRITCHARD, ROBERT EMLYN -1

机译：在中等超声速下最大升降比比翼型上的基本拉力效应
6. Drag force as a function of cross section and angle of attack. A hydraulic laboratory dataset for numerical validation [O] . Cian J. Desmond, Florent Thiebaut, Jimmy Murphy 2019

机译：阻力与横截面和攻角的关系。用于数值验证的液压实验室数据集
7. Measurements of the pressure distributions on two circular cylinders of diameter d, vertically immersed in a turbulent boundary layer, are performed for various cylinder spacings s and angles of attack φ. The characteristics of the drag and lift forces acting on the cylinder are classified into three regions : i.e., 1) 0°＜__〜φ＜__〜30°, 2) 30°＜__〜φ＜__〜120°and 3) 120°＜__〜φ＜__〜180°which are divided by the two zero-lift force lines. Moreover, it is found that the interference between two cylinders is almost negligible for s/d＞__〜4, except for the influence of the wake region of the upstream cylinder. [O] . 谷口清一, 坂本弘志, Seiichi TANIGUCHI, 1980

机译：对于不同的气缸间距s和迎角φ，对垂直浸入湍流边界层的直径为d的两个圆柱上的压力分布进行测量。作用在气缸上的阻力和提升力的特性分为三个区域：1）0°＜__ 〜φ ＜__ 〜30°，2）30°＜__ 〜φ ＜__ 〜120°和3） 120°＜__ 〜φ ＜__ 〜180°除以两条零升力线。而且，发现除了上游气缸的尾流区域的影响之外，对于s / d＞ __〜4，两个气缸之间的干扰几乎可以忽略。
8. Flight investigation from high subsonic to supersonic speeds to determine the zero-lift drag of a transonic research vehicle having wings of 45 degree sweepback, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections [R] . Katz, Ellis 1949

机译：从高亚音速到超音速的飞行调查，以确定具有45度后掠翼，纵横比4，锥度比0.6和NaCa 65a006翼型截面的跨音速研究车辆的零升力阻力

Lift and Drag of Non-conventional Wings at Subsonic Speeds and Zero Angle of Attack - An Experimental Investigation

著录项

引文网络

相似文献

相关主题

期刊订阅