Streamwise momentum analysis of subsonic wall interference on flat-plate wings at high angles of attack

Abstract

Effects of solid wind tunnel walls on wings at high angles of attack are evaluated from the conservation of mass and momentum. It is assumed that the difference between the upstream and downstream axial momenta is balanced by an increment of axial force exerted on the model by the surrounding fluid. The increment of lateral force is evaluated using the observation that for highly separated flows the angle between the aerodynamic force and the wing surface is constant.