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Reduction of induced drag in conguration flight using wing twist at post-stall angles of attack
Published in American Institute of Aeronautics and Astronautics Inc, AIAA
2016
Abstract
In this paper, a novel decambering technique has been implemented using a vortexlattice method to study the effects of wing twist on the induced drag of individual lifting surfaces in congurationight. The effects of both geometric and aerodynamic twist arestudied. 2D Cl−α and Cm−α from XFoil at Re = 1×106for NACA0012 airfoil is used as inputto predict 3D post-stall aerodynamic characteristics for a single wing with geometric twistand compared with literature. Aerodynamic twist is implemented by using dierent airfoilsalong wing-span and wing CL−α and Cdi−α aare compared with experiment. The effect ofasymmetric aerodynamic twist on the leading wing shows distinct changes in the span-wisedistribution of Cland Cdion the trailing wing and throws up interesting inferences aboutformation ight aerodynamics. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA, All rights reserved.
About the journal
JournalData powered by Typeset54th AIAA Aerospace Sciences Meeting
PublisherData powered by TypesetAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISSN0001-1452
Impact Factor1.868
Open AccessNo
Citation Styleunsrt
Sherpa RoMEO Archiving PolicyGreen
Concepts (14)
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    Aerodynamics
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    Aerospace engineering
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    Angle of attack
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    Aviation
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    Drag
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    Drag reduction
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    AERODYNAMIC CHARACTERISTICS
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    INDUCED DRAG
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    LIFTING SURFACES
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    STALL ANGLES
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    VORTEX LATTICE METHOD
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    WING SPAN
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    WING TWIST
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    Aerodynamic stalling