Department of mechanical engineering college of science and technology Nihon University.
出版者
宇宙科学研究所
出版者（英）
Institute of Space and Astronautical Science
雑誌名
The Institute of Space and Astronautical Science report. S.P. : Proceedings of the Symposium on Mechanics for Space Flight
巻
1
ページ
41 - 50
発行年
1983-03
抄録（英）
A numerical study is presented for the transonic flow over a two-dimensional airfoil oscillating in pitch at the moderately high mean value of the angle of attack. Stressed is the understanding of the frequency effect on the surface pressure characteristics against the instantaneous angle of attack, due to the interaction between the shock-wave and the after-shock separated boundary layer. An implicit factored finite-difference method developed by Beam & Warming is applied to the compressible Navier-Stokes equations. The remarkable improvement of the computation speed is achieved with the program vectorization suitable for CRAY 1-S. The computational results are compared with the experimental data measured at the NASA-Ames 11-by-11 Foot Wind Tunnel.
Frequency Effet of Transonic Flow Over an Oscillating Airfoil
SA0033403.pdf
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