Drag optimization for transport aircraft Mission Adaptive Wing

Abstract

A direct optimization study was performed to produce a preliminary evaluation of the potential benefits of a mission adaptive wing employing variable camber technology in typical jet transport aircraft missions, in terms of fuel efficiency increase directly obtainable from airfoil viscous drag reduction alone. A 2-D airfoil analysis approach was adopted, associated with an idealized variable camber mechanism based on elastic deformation and surface extension. Using a direct function optimization program coupled to a viscous-inviscid airfoil analysis routine, optimized variable camber configurations were obtained for several weight conditions of a typical transport aircraft along a sub-critical cruise mission leg. Independent runs were executed considering only trailing and both leading and trailing-edge camber variation and, for each of them, an integrated range parameter has been obtained, proportional to the maximum possible aircraft range. Results indicate that the range increases up to 7.03% over the base airfoil that could be reached with camber variation in the trailing edge region only, and up to 24.6% when leading edge adaptation was considered simultaneously. However, pressure distribution results indicate that the high leading-edge curvatures required for that would probably decrease cruise critical Mach. On other hand, the trailing-edge only approach may offer better conditions for supercritical cruise

Aircraft drag reduction—a review

“…They deserve serious research effort(s) utilizing modern design optimization technology (e.g. see references [273] to [277]).…”

Study on a Camber Adaptive Winglet

“…1. The airfoil sections camber changes are based on the morphing mechanism developed by Martins and Catalano [17]. In this proposed construction, the airfoil sections are able to change the leading and trailing edges angles.…”

“…Optimizing the winglet geometry for different flight condtions would bring reduction of the airplane total drag, improving the aircraft performance. Martins and Catalano [17] developed a morphing mechanism capable of changing the angle of the leading and trailing edge of the airfoil fixing the central part, see Fig. 1.…”

Aircraft drag reduction—a review

“…They deserve serious research effort(s) utilizing modern design optimization technology (e.g. see references [273] to [277] Boundary control by local heating of the wall. In…”