Improved Flutter Boundary Prediction for an Isolated Two-Degree-of-Freedom Airfoil

被引：8
|
作者：
Schwarz, Jordan B. [1 ]
Dowell, Earl H. [1 ]
Thomas, Jeffrey P. [1 ]
Hall, Kenneth C. [1 ]
Rausch, Russ D. [2 ]
Bertels, Robert E. [2 ]
机构：
[1] Duke Univ, Dept Mech Engn & Mat Sci, Durham, NC 27708 USA
[2] NASA, Langley Res Ctr, Aeroelast Branch, Hampton, VA 23681 USA
来源：
JOURNAL OF AIRCRAFT | 2009年 / 46卷 / 06期
关键词：
D O I：
10.2514/1.30703
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A novel method of computing the flutter boundary for all isolated airfoil based on a high-fidelity computational fluid dynamics model reveals unusual behavior in a critical transonic range. Inviscid and viscous predictions of the flutter boundary for the two airfoils examined differ substantially in this critical region and become sensitive to Mach number and grid topology due to complicated shock/boundary-layer interactions. Computational fluid dynamics predictions of the flutter boundary for a NACA 0012 section airfoil are also compared with previous experimental results.
引用
收藏
页码：2069 / 2076
页数：8
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