AN EXPLORATORY WIND-TUNNEL INVESTIGATION OF THE WAKE EFFECT OF A PANEL TIP-MOUNTED FAN-JET ENGINE ON THE LIFT-INDUCED VORTEX

摘要

An investigation has been conducted in the Langley 8-foot transonic pressure tunnel to determine the effectiveness of a tip-mounted powered-model high-bypass fan-jet engine in reducing the tip vorticity of an unswept symmetrical panel. The effects of end plates, a body of revolution, and a flow-through nacelle on panel-tip vorticity were also determined for comparison. All tests were conducted at a Mach number of 0.70, at angles of attack from approximately 0° to 4°, and at a Reynolds number of 3.82 x 106 based on the mean geometric chord of 33.17 centimeters.