Preprint Article Version 1 NOT YET PEER-REVIEWED

Wing Tip Drag Reduction at Nominal Take-Off Mach Number: An Approach to Local Active Flow Control with a Highly Robust Actuator System

  1. NAVASTO GmbH, 10587 Berlin, Germany
  2. Technische Universitaet Berlin, 10587 Berlin, Germany
  3. Deutsches Zentrum fuer Luft- und Raumfahrt e.V. (DLR), 38108 Braunschweig, Germany
Version 1 : Received: 19 July 2016 / Approved: 20 July 2016 / Online: 20 July 2016 (04:09:12 CEST)

A peer-reviewed article of this Preprint also exists.

Bauer, M.; Grund, T.; Nitsche, W.; Ciobaca, V. Wing Tip Drag Reduction at Nominal Take-Off Mach Number: An Approach to Local Active Flow Control with a Highly Robust Actuator System. Aerospace 2016, 3, 36. Bauer, M.; Grund, T.; Nitsche, W.; Ciobaca, V. Wing Tip Drag Reduction at Nominal Take-Off Mach Number: An Approach to Local Active Flow Control with a Highly Robust Actuator System. Aerospace 2016, 3, 36.

Journal reference: Aerospace 2016, 3, 36
DOI: 10.3390/aerospace3040036

Abstract

This paper discusses wind tunnel test results aimed at advancing active flow control technology to increase the aerodynamic efficiency of an aircraft during take-off. A model of the outer section of a representative civil airliner wing was equipped with two-stage fluidic actuators between the slat edge and wing tip, where mechanical high-lift devices fail to integrate. The experiments were conducted at a nominal take-off Mach number of M = 0.2. At this incidence velocity, separation on the wing section, accompanied by increased drag, is triggered by the strong slat edge vortex at high angles of attack. On the basis of global force measurements and local static pressure data, the effect of pulsed blowing on the complex flow is evaluated, considering various momentum coefficients and spanwise distributions of the actuation effort. It is shown that through local intensification of forcing, a momentum coefficient of less than cμ = 0.6% suffices to offset the stall by 2.4°, increase the maximum lift by more than 10%, and reduce the drag by 37% compared to the uncontrolled flow.

Subject Areas

flow control; leading edge; fluidic actuator

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