Patent ID: 8336813

Claim:
A engine pylon for suspending a turbo engine from a wing of an aircraft, said turbo engine having a vertical mid-plane passing through its longitudinal axis, said engine pylon comprising two lateral faces, of which one of the lateral faces is directed toward the root of said wing and the other of the lateral faces is directed toward a distal end of said wing, said lateral faces converging to form a trailing edge at a rear of said engine pylon, and a lower part of said rear of the engine pylon supporting and directly connected to a hot stream nozzle of said turbo engine such that said lower part of the rear of the engine pylon is swept by a cold stream of this turbo engine, wherein at least said lower part of the rear of the engine pylon is curved toward the root of said wing so that at least said trailing edge part of said lower part is shifted toward said root with respect to said vertical mid-plane.