Compression Pylon Reduces Interference Drag

Abstract

New design reduces total drag by 4 percent. Pylon reduces fuselage/wing/pylon/nacelle-channel compressibility losses without creating additional drag associated with other areas of pylon. Minimum cross-sectional area of channel occurs at trailing edge of wing. Velocity of flow in channel always nearly subsonic, reducing compressibility losses associated with supersonic flow. Flow goes past trailing edge before returning to ambient conditions, resulting in no additional drag to aircraft. Designed to compress flow beneath wing by reducing velocity in this channel, thereby reducing shockwave losses and providing increase in wing lift.