2014 Volume 12 Issue APISAT-2013 Pages a9-a16
This paper presents computational and experimental results on investigation of noise generation from the flap side-edge for high-lift device noise research models in JAXA. The main purpose of this paper is focused on investigation of the differences of the flow field between the models with and without the swept angle and taper-ratio of the wing by comparison of the computational results. In the case of wings with the swept angle and taper-ratio, the flap is deployed in a three-dimensional direction based on the wing planform. The changes of the behaviors of the vortices from the flap side-edge and resulting pressure fluctuations due to the flap deployment are shown.
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN
