Please use this identifier to cite or link to this item: http://hdl.handle.net/11455/72255
標題: 等加速度上仰機翼動態失速之流場觀察
作者: 陳志敏
闕河誠
關鍵字: 上仰機翼;動態失速渦流;剪力層渦流
出版社: 國立中興大學工學院;Airiti Press Inc.
Project: 興大工程學報, Volume 8, Issue 2, Page(s) 75-84.
摘要: 
本文主要是在風洞中以煙線觀察 NACA 0015 機翼於不同的加速度上仰過程中,
其翼面附近及尾流區渦流結構之變化與差異。流場觀察結果有助於了解等速上仰機翼中的初
始加速度對動態失速渦流之形成、發展及移動的影響。經由本實驗發現,對於等加速度上仰
的機翼,似乎可以找到一個對應的速度值,使得它們在相同的上仰角度下,具有相似的流場
結構。文中詳細討論上仰機翼升力表面動態失速渦流與剪力層渦流的發展和互相抑制的現象
,並比較等加速度或等速度對這些現象的影響。

Flow visualization of the vortical structures developed on a NACA 0015
airfoil pitching at constant acceleration has been studied in a wind tunnel. The
observations of the experiments may be benificial to the understanding of
initial acceleration effects on the development of the dynamic stall vortex that
occurs on a constant-rate pitching-up airfoil. It is found that for the case of
airfoil piching at a constant acceleration rate in the range studied there
exists a corresponding case of constant pitch rate, such that both the cases
have nearly identical flow structure at the same angle of attack. The effects of
acceleration and pitch rates on the dynamic stall vortex and shear layer
vortices are also discussed.
URI: http://hdl.handle.net/11455/72255
ISSN: 1017-4397
Appears in Collections:第08卷 第2期
工學院

Show full item record
 
TAIR Related Article

Google ScholarTM

Check


Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.