首页> 美国政府科技报告 >Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - leading-edge flaps deflected

【24h】

Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - leading-edge flaps deflected

机译：风洞探测马赫数从0.50到1.29的未扫描，纵横比为2.67的锥形翼，带有前缘和后缘襟翼 - 前缘襟翼偏转

获取原文

页面导航

摘要
著录项
相似文献
相关主题

摘要

No Abstract Available

著录项

作者
Stivers, Louis S , Jr; Malick, Alexander W;
展开▼
作者单位

展开▼
年度 1951
页码 1-42
总页数 42
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词

相似文献

外文文献
中文文献
专利

1. Effects of Leading- and Trailing-Edge Gurney Flaps on a Delta Wing [J] . Lance W. Traub, Samuel F. Galls Journal of Aircraft . 1999,第4期

机译：前缘和后缘格尼襟翼对三角翼的影响
2. The effect of aspect ratio on the leading-edge vortex over an insect-like flapping wing [J] . Phillips Nathan, Knowles Kevin, Bomphrey Richard J. Bioinspiration & biomimetics . 2015,第5期

机译：纵横比对像昆虫一样拍打的机翼前缘涡流的影响
3. Wind-Tunnel Testing of Rotor with Individually Controlled Trailing-Edge Flaps for Vibration Reduction [J] . Beatrice Roget, Inderjit Chopra Journal of Aircraft . 2008,第3期

机译：带有独立控制后缘襟翼的转子风洞测试，用于减振
4. Aerodynamic Optimization of Mach 0.745 Transonic Truss-Braced Wing Aircraft with Variable-Camber Continuous Trailing-Edge Flap [C] . Juntao Xiong, Robert E. Bartels, Nhan Nguyen AIAA SciTech Forum and Exposition . 2021

机译：MACH 0.745跨安桁架支架翼飞机的空气动力学优化，可变弧形连续后缘襟翼
5. Experimental investigation of wing flexibility on force generation of a hovering flapping wing micro air vehicle with double wing clap-and-fling effects [O] . Quoc V Nguyen, Woei L Chan, Marco Debiasi 2017

机译：双翼拍摄杂交效应悬停翼微型空气车辆翼韧性翼柔性的实验研究

Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - leading-edge flaps deflected

摘要

著录项

相似文献

相关主题

期刊订阅