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Dynamic Stall Control Investigations on a Full Size Chord Blade Section

Geißler, W. and Dietz, G. and Mai, H. and Junker, B. and Lorkowski, Th. (2004) Dynamic Stall Control Investigations on a Full Size Chord Blade Section. European Rotorcraft Forum, Marseille, France, 14-16 September 2004, 2004-09-14-2004-09-16, Marseille, France.

Full text not available from this repository.

Abstract

In the present investigations dynamic stall is controlled by a nose-drooping device, where the 10%-sealed leading edge part of a new supercritical airfoil section drooped down dynamically during the pitching motion of the blade model to alleviate dynamic stall. Both CFD-calculations as well as experiments have been accomplished for these investigations within the scope of the project ADASYS (Adaptive Systems) between the partners: ECD, EADS and DLR. Three different DLR-Institutes were involved in the project: Institute of Aerodynamic and Flow Technology, Institute of Aeroelasticity, both located in Göttingen and Institute of Flight Systems located in Braunschweig, Germany. Main emphasis in the present discussions is placed on the experimental investigations which have been carried out in the DNW-TWG wind tunnel facility located at DLR-Göttingen. A full size 0,3m chord blade section with 1m span (between the tunnel side walls) has been installed inside the adaptive wall test section of this tunnel. The model made of composite material was suspended in the forced pitch-oscillation test rig of the DLR-Institute of Aeroelasticity. In addition to the pitching motion of the model about its quarter chord axis, the 10% leading edge part (0,5m span) of the model was oscillated separately from the blade motion in different drooping modes and with phase-variations between blade motion and flap motion. The leading edge deflection has been achieved with piezoelectric actuator devices developed by EADS. the flap/actuator arrangement has been designed as a separate module which could easily be removed from the remainder of the model. In the present paper experimental results and comparisons with numerical data are discussed for steady as well as unsteady flow cases.

Item URL in elib:https://elib.dlr.de/14481/
Document Type:Conference or Workshop Item (Paper)
Additional Information: LIDO-Berichtsjahr=2005,
Title:Dynamic Stall Control Investigations on a Full Size Chord Blade Section
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Geißler, W.UNSPECIFIEDUNSPECIFIED
Dietz, G.UNSPECIFIEDUNSPECIFIED
Mai, H.UNSPECIFIEDUNSPECIFIED
Junker, B.UNSPECIFIEDUNSPECIFIED
Lorkowski, Th.UNSPECIFIEDUNSPECIFIED
Date:2004
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:dynamic stall, supercritical airfoil, nose-drooping, ADASYS
Event Title:European Rotorcraft Forum, Marseille, France, 14-16 September 2004
Event Location:Marseille, France
Event Type:international Conference
Event Dates:2004-09-14-2004-09-16
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:Rotorcraft (old)
DLR - Research area:Aeronautics
DLR - Program:L RR - Rotorcraft Research
DLR - Research theme (Project):L - The Active Rotorcraft (old)
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity
Deposited By: Erdmann, Daniela
Deposited On:16 Sep 2005
Last Modified:14 Jan 2010 21:54

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