Adaptive load redistribution using mini-TEDs

Abstract

This article describes work in the DLR high performance flexible aircraft project to investigate mini trailing edge devices for adaptive load redistribution. The EU project AWIATOR showed the potential of mini-TEDs, but the increased rear wing loading and resulting nose-down pitching moment require further investigation. 2-D computations were carried out to investigate effective split-flap deployment angles. The calculations show that the optimal height of a mini-TED on an unknown profile in transonic flow cannot be predicted by scaling with the boundary layer thickness on the pressure-side trailing edge. The scope of the future work on structure-coupled 3-D computations on a trimmed aircraft is described.