2024-03-28T10:22:30Z
https://nagoya.repo.nii.ac.jp/oai
oai:nagoya.repo.nii.ac.jp:00012001
2023-01-16T03:58:17Z
320:321:322
境界層の超音速パネルフラッタへの影響
Effects of Boundary Layer on Supersonic Panel Flutter
橋本, 敦
HASHIMOTO, Atsushi
八木, 直人
YAGI, Naoto
中村, 佳朗
NAKAMURA, Yoshiaki
open access
Panel Flutter
Fluid-Structure Coupled Problem
CFD-CSD Coupling
Supersonic Boundary Layer
A fluid-structure coupled computation code has been developed and applied to a panel flutter problem. The flutter velocities and the amplitudes of limit cycle oscillations obtained using the present method agree well with those of Dowell. It is found that the boundary layer over the panel can suppress flutter particularly in the Mach number region between 1.2 and 1.35, the effect of which increases with viscosity. In a 3D problem, good agreement was obtained between computation and experiment.
日本航空宇宙学会
2007-04-05
jpn
journal article
VoR
http://hdl.handle.net/2237/13877
https://nagoya.repo.nii.ac.jp/records/12001
1344-6460
日本航空宇宙学会論文集
55
639
159
164
https://nagoya.repo.nii.ac.jp/record/12001/files/jjsass_v55_n639.pdf
application/pdf
1.1 MB
2018-02-20