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Effect of Sweep on a Pitching Finite Wing

Gardner, Anthony D. and Merz, Christoph B. and Wolf, C. Christian (2019) Effect of Sweep on a Pitching Finite Wing. Journal of the American Helicopter Society, 64 (3), pp. 1-13. American Helicopter Society. doi: 10.4050/JAHS.64.032007. ISSN 0002-8711.

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Official URL: https://doi.org/10.4050/JAHS.64.032007


An investigation was performed into the effect of positive and negative sweep angle on the boundary layer transition and dynamic stall behaviour of a finite wing. The finite wing had a 6:1 aspect ratio, modern (SPP8) tip shape and positive twist, moving the maximum load on the wing away from the wind tunnel wall. Experiments were performed with sweep Lambda=+-30° and Lambda=0° for static polars and sinusoidal pitching. The positively twisted wing shows a similar S-shaped boundary layer transition on the pressure side to that previously seen for helicopter rotor blades in hover. The transition positions on the suction side of the wing are comparable for the same local angle of attack at all values of the sweep Lambda at each of the three pressure sections, and for dynamic pitching motions a hysteresis around the static transition positions is seen. Sweeping the wing led to later stall and higher maximum lift for both static polars and dynamic stall, except for a single case. The negative aerodynamic damping is worse for the swept wing than for the unswept wing, except where the delay of stall led to the flow remaining attached.

Item URL in elib:https://elib.dlr.de/126911/
Document Type:Article
Title:Effect of Sweep on a Pitching Finite Wing
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Gardner, Anthony D.anthony.gardner (at) dlr.dehttps://orcid.org/0000-0002-1176-3447
Merz, Christoph B.Daimler AGUNSPECIFIED
Wolf, C. ChristianChristian.Wolf (at) dlr.dehttps://orcid.org/0000-0002-9052-7548
Date:1 July 2019
Journal or Publication Title:Journal of the American Helicopter Society
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
DOI :10.4050/JAHS.64.032007
Page Range:pp. 1-13
EditorsEmailEditor's ORCID iD
Publisher:American Helicopter Society
Keywords:swept wing, boundary layer transition, unsteady aerodynamics
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:rotorcraft
DLR - Research area:Aeronautics
DLR - Program:L RR - Rotorcraft Research
DLR - Research theme (Project):L - The Virtual Aerodynamic Rotorcraft (old)
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Helicopter, GO
Deposited By: Winkels, Elisabeth
Deposited On:17 Sep 2019 17:01
Last Modified:17 Sep 2019 17:01

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