S.-Y. Lin, Y.-S. Chin

Reduction of noise due to transonic blade-vortex interaction is investigated numerically. In this paper, we attempt to reduce two dominant sound waves, transonic and compressibility, in the blade-vortex interaction. Two control techniques used are the blowing / suction and porous wall on the airfoil surface. Numerical results indicate that the blowing / suction control technique reduces the fluctuations generated by the transonic wave but has little influence on the compressibility wave unless it is employed at the leading edge of the blade. As for the surface porosity control, the results are satisfactory on reduction of both the compressibility and transonic waves.

First Joint CEAS/AIAA Aeroacoustics Conference, München, 1995

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1995, 1995-01, First Joint CEAS/AIAA Aeroacoustics Conference - Proceedings; S.347-356; 1995; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroacoustics

Bibliothek

1995