Numerical Study for Interactions Between Separation on Supersonic Flow and Laser-Induced Blast Wave

Abstract

Flow separation on an airfoil was numerically reproduced by integrating a two-dimensional Navier-Stokes equation. We found that the flow separation on the upper surface of the airfoil was suppressed when repetitive pulses were irradiated to the undersurface. An expansion region was induced at a trailing edge of the wing when the blast wave propagated from the under- to upper surfaces. The separation region became smaller because an inverse pressure gradient on the upper surface was relaxed when the expansion wave at the trailing edge interacted with the separation region. A new contactless flow control technique proposed by us was effective to improve an aerodynamic performance of the wing.