Patent ID: 8251306

Claim:
An aircraft comprising: a body; a pair of wings affixed to an upper portion of the body; a pair of airfoils mounted to a lower portion of the body; and a pair of bypass turbofan engines each of said engines being mounted to one of the wings, wherein each engine comprises a module comprising a generally elongated casing, a central portion extending through the length of the module for exhausting the hot exhaust gas from the engine, and a peripheral portion surrounding the central portion for the bypass air from the engine; wherein the casing includes at least one outlet provided from the peripheral portion of the module through the casing to enable a portion of the bypass air to be separated from a remainder of the bypass air and to be directed out of the module in a direction towards the body and at an angle relative to the axis of the module; wherein the engines and modules are arranged so that at least part of the portion of the bypass air directed out of each module flows over at least part of an upper surface of one of the airfoils when the aircraft travels at a predetermined speed.