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Numerical Assessment of a High‐Lift Configuration with Circulation Control and flexible Droop Nose

Burnazzi, Marco and Keller, Dennis (2015) Numerical Assessment of a High‐Lift Configuration with Circulation Control and flexible Droop Nose. DLR Symposium "High-Lift System Research - Celebrating 10 Years of DLR-F15", 7.-9. Dezember 2015, Braunschweig, Deutschland.

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The use of active flow control in high-lift systems is a promising solution to improve aircraft low-speed capabilities and reduce noise emissions during landing. To date, however, the system power requirements have been too high in relation to the achieved lift gains, to allow a large use of these technologies in the aeronautical industry. The present work addresses this problem by developing and testing a leading-edge device to increase the efficiency of an internally-blown Coanda-flap configuration. The main objectives are the increase of the stall angle of attack and the reduction of the jet momentum requirements. A 2D sensitivity analysis is performed to explore the effects of varying the airfoil camber and thickness in the first 20% of the airfoil chord. The resulting droop-nose configuration yields a reduction of 32% of the jet momentum required to achieve a target maximum lift coefficient of 5.0, while improving the stall angle by 10°. As the modified leading edge geometry presents different stall mechanisms, the aerodynamic response to variations of jet momentum is also different. In particular, for a jet momentum coefficient above 0.035 the stall angle of attack increases with jet momentum, in contrast to the behavior observed with the baseline leading-edge configuration. Subsequent to the 2D study, the results are tested on a wing-body configuration with a circulation controlled plain flap, which is deflected by 65°. Therefore, calculations at an identical blowing coefficient are performed on the clean-nose and droop-nose configurations. The comparison of the 3D results verifies the stall delay observed in 2D. The outboard leading edge stall seen on the clean-nose configuration is successfully suppressed. In contrast, the maximum lift of the droop-nose configuration is limited due to fuselage-wing integration effects. As a result, the increase of the maximum lift coefficient is limited to 3%, whereas the maximum angle of attack is raised by 10°.

Item URL in elib:https://elib.dlr.de/119901/
Document Type:Conference or Workshop Item (Speech)
Title:Numerical Assessment of a High‐Lift Configuration with Circulation Control and flexible Droop Nose
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Burnazzi, MarcoMarco.Burnazzi (at) dlr.deUNSPECIFIED
Keller, DennisDennis.Keller (at) dlr.dehttps://orcid.org/0000-0002-1471-9433
Date:December 2015
Refereed publication:No
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Keywords:CFD, TAU, high-lift, circulation control, droop nose, aerodynamics, F15
Event Title:DLR Symposium "High-Lift System Research - Celebrating 10 Years of DLR-F15"
Event Location:Braunschweig, Deutschland
Event Type:Other
Event Dates:7.-9. Dezember 2015
Organizer:DLR Institut für Aerodynamik und Strömungstechnik
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Simulation and Validation (old), L - Flight Physics (old)
Location: Braunschweig , Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Transport Aircraft
Institute for Aerodynamics and Flow Technology > CASE, GO
Deposited By: Keller, Dennis
Deposited On:18 Jun 2018 09:22
Last Modified:31 Jul 2019 20:17

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