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Effects of leading and trailing edge flaps on the aerodynamics of airfoil/vortex interactionsA numerical procedure has been developed for predicting the two-dimensional parallel interaction between a free convecting vortex and a NACA 0012 airfoil having leading and trailing edge integral-type flaps. Special emphasis is placed on the unsteady flap motion effects which result in alleviating the interaction at subcritical and supercritical onset flows. The numerical procedure described here is based on the implicit finite-difference solutions to the unsteady two-dimensional full potential equation. Vortex-induced effects are computed using the Biot-Savart Law with allowance for a finite core radius. The vortex-induced velocities at the surface of the airfoil are incorporated into the potential flow model via the use of the velocity transpiration approach. Flap motion effects are also modeled using the transpiration approach. For subcritical interactions, our results indicate that trailing edge flaps can be used to alleviate the impulsive loads experienced by the airfoil. For supercritical interactions, our results demonstrate the necessity of using a leading edge flap, rather than a trailing edge flap, to alleviate the interaction. Results for various time-dependent flap motions and their effect on the predicted temporal sectional loads, differential pressures, and the free vortex trajectories are presented
Document ID
19950039582
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Hassan, Ahmed A.
(McDonnell Douglas Helicopter Company, Mesa, AZ United States)
Sankar, L. N.
(Georgia Inst. of Technology, Atlanta, GA United States)
Tadghighi, H.
(McDonnell Douglas Helicopter Company, Mesa, AZ United States)
Date Acquired
August 16, 2013
Publication Date
April 1, 1994
Publication Information
Publication: American Helicopter Society, Journal
Volume: 39
Issue: 2
ISSN: 0002-8711
Subject Category
Aerodynamics
Accession Number
95A71181
Funding Number(s)
CONTRACT_GRANT: NAS1-19136
Distribution Limits
Public
Copyright
Other

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