Control of vortical lift on delta wings by tangential leading-edge blowing

Abstract

An experiment has been performed to examine the feasibility of vortex control by tangential mass injection at the leading edge of a 60 deg delta wing. The initial results indicate that direct control of the primary separation allows significant control of the vortex flow up to angles of attack of 60 deg. At lower angles of attack, the vortical flow may be removed entirely from the surface of the wing, recovering the fully attached flow case. The effects of the mass injection have been shown to be decoupled from the geometric angle of attack, allowing the possibility for controlling lift without changing attitude. Nomenclature b =wing semispan c =wing root chord Cg' = spanwise sectional rolling moment coefficient CL' = wing rolling moment coefficient Cn = spanwise sectional normal force coefficient CN = wing normal force coefficient Cp = pressure coefficient CM = bio wing momentum coefficient CM * = crossflow blowing momentum coefficient h = slot height Vj =jet velocity Fw = freestream velocity ae = effective angle of attack oig = geometric angle of attack e = wing semi apex angle