首页> 外文OA文献 >Flutter characteristics of thin airfoils in pitching oscillation. 3rd Report. The range of attack angle where leading edge stall separation occurs during oscillation.

【2h】

Flutter characteristics of thin airfoils in pitching oscillation. 3rd Report. The range of attack angle where leading edge stall separation occurs during oscillation.

机译：螺旋振荡中薄翼型的颤动特性。第三次报告。在振荡期间发生前导边缘分离的攻击角度。

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
相似文献
相关主题

著录项

作者
Hiroyuki UENO; Hideo TANAKA; Ichiro FUJIMOTO;
展开▼
作者单位

展开▼
年度 1987
总页数
原文格式 PDF
正文语种
中图分类

相似文献

外文文献
专利

1. Thin airfoil load control during post-stall and large pitch angles using leading-edge trips [J] . Leknys R. R., Arjomandi M., Kelso R. M., Journal of Wind Engineering and Industrial Aerodynamics: The Journal of the International Association for Wind Engineering . 2018,第期

机译：薄翼型载荷控制在后档和使用前沿跳闸的大俯仰角度
2. EFFECTS OF COMPRESSIBILITY, PITCH RATE, AND REYNOLDS NUMBER ON UNSTEADY INCIPIENT LEADING-EDGE BOUNDARY LAYER SEPARATION OVER A PITCHING AIRFOIL [J] . Choudhuri PG., Knight DD. Journal of Fluid Mechanics . 1996,第0期

机译：可压缩性，俯仰率和雷诺数对俯仰翼型上非定常渐近前沿边界层分离的影响
3. Dynamic Thin-Airfoil Stall and Leading-Edge Stall of Oscillating Wings at Low Reynolds Number [J] . Fan Chengwei, Wu Yadong, Yu Yuelong, Fluid Dynamics . 2019,第5期

机译：动态薄翼型在低雷诺数摆动振荡翼的旋转档位
4. Stall Detection on a Leading- Edge Plasma Actuated Pitching Airfoil Utilizing Onboard Measurement [C] . P. Bowles, T. Corke, E. Matlis AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition . 2009

机译：利用机载测量对前沿等离子驱动俯仰翼型进行失速检测
5. Unsteady aerodynamic characteristics of abrupt stall type airfoil in pitching oscillation near stall angle of attack (1st report, On dynamic characteristics of flow separation and regions corresponding to separation patterns) [O] . Susumu ISHII, Hideo TANAKA, Ichiro FUJIMOTO 1985

机译：突然空气动力学特性突然间翼型螺旋振荡旋转震荡附近的攻击角度（第一报告，关于流动分离的动态特性及其对应于分离图案的区域）
6. Calculation of lift and pitching moments due to angle of attack and steady pitching velocity at supersonic speeds for thin sweptback tapered wings with streamwise tips and supersonic leading and trailing edges [R] . Martin, John C, Margolis, Kenneth, Jeffreys, Isabella 1952

机译：对于具有流向尖端和超音速前缘和后缘的薄后掠锥形翼，在超音速下计算由迎角和稳定俯仰速度引起的升力和俯仰力矩

Flutter characteristics of thin airfoils in pitching oscillation. 3rd Report. The range of attack angle where leading edge stall separation occurs during oscillation.

著录项

相似文献

相关主题

期刊订阅