BUFFET INTENSITY REDUCTION OF A COMBAT AIRCRAFT WING

摘要

The results of a computational and experimental investigation of a separated flow over a container installed at the end section of a combat airplane wing are presented. It was shown that oscillation of the flow separation line on the surface container is the reason for the increased torsional vibrations of the container. The computations and the tests in the TsAGI wind tunnel have demonstrated that the installation of a plate fixing the separation line on the container surface along the generatrix is an effective means of reducing the vibrations of a container with a wing.