热科学学报（英文版）2012，Vol.21Issue(5)：435-440,6.DOI:10.1007/s11630-012-0565-y
Effects of Aspect Ratio in a Transonic Shock Tube Airfoil Flow
Effects of Aspect Ratio in a Transonic Shock Tube Airfoil Flow
Masashi KASHITANI 1Keita MIURA 1Shinichiro NAKAO 2Yutaka YAMAGUCHI2
作者信息
- 1. Department of Aerospace Engineering, National Defense Academy, 1-10-20 Hashirimizu, Yokosuka, 239-8686, JAPAN
- 2. Department of Mechanical Engineering, Nagasaki Institute of Applied Science, 536 Aba-Machi, Nagasaki, 851-0193, JAPAN
- 折叠
摘要
关键词
Shock tube/Aerodynamics/Transonic flows/Aspect ratio/Wind tunnel correctionKey words
Shock tube/Aerodynamics/Transonic flows/Aspect ratio/Wind tunnel correction引用本文复制引用
Masashi KASHITANI,Keita MIURA,Shinichiro NAKAO,Yutaka YAMAGUCHI..Effects of Aspect Ratio in a Transonic Shock Tube Airfoil Flow[J].热科学学报（英文版）,2012,21(5):435-440,6.
