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Effects of leading and trailing edge flaps on the aerodynamics of airfoil/vortex interactionsA numerical procedure based on the unsteady 2D full potential equation is presently used to simulate the effects of leading-edge and trailing-edge flaps on the aerodynamics of airfoil-vortex interactions. Attention is given to unsteady flap-motion effects, which alleviate those interactions at sub- and supercritical onset flows. For subcritical interactions, the results obtained indicate that trailing-edge flaps can be used to alleviate the impulsive loads experienced by the airfoil; for supercritical interactions, a leading- rather than trailing-edge flap must be used to alleviate the interaction.
Document ID
19920064333
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hassan, Ahmed A.
(McDonnell Douglas Helicopter Co. Mesa, AZ, United States)
Sankar, L. N.
(Georgia Institute of Technology Atlanta, United States)
Tadghighi, H.
(McDonnell Douglas Helicopter Co. Mesa, AZ, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Meeting Information
Meeting: AHS International Specialists'' Meeting on Rotorcraft Basic Research
Location: Atlanta, GA
Country: United States
Start Date: March 25, 1991
End Date: March 27, 1991
Accession Number
92A46957
Funding Number(s)
CONTRACT_GRANT: NAS1-19136
Distribution Limits
Public
Copyright
Other

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