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Control of the boundary layer separation about an airfoil by active surface heatingApplication of active control to separated flow on the RC(6)-08 airfoil at high angle of attack by localized surface heating is numerically simulated by integrating the compressible two-dimensional nonlinear Navier-Stokes equations solver. Active control is simulated by local modification of the temperature boundary condition over a narrow strip on the upper surface of the airfoil. Both mean and perturbed profiles are favorably altered when excited with the same natural frequency of the shear layer by moderate surface heating for both laminar and turbulent separation. The shear layer is found to be very sensitive to localized surface heating in the vicinity of the separation point. The excitation field at the surface sufficiently altered both the local as well as the global circulation to cause a significant increase in lift and reduction in drag.
Document ID
19880061651
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Maestrello, Lucio
(NASA Langley Research Center Hampton, VA, United States)
Badavi, Forooz F.
(PRC Kentron, Inc. Hampton, VA, United States)
Noonan, Kevin W.
(U.S. Army, Aerostructures Directorate, Hampton VA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 88-3545
Meeting Information
Meeting: AIAA, ASME, SIAM, and APS, National Fluid Dynamics Congress
Location: Cincinnati, OH
Country: United States
Start Date: July 25, 1988
End Date: July 28, 1988
Accession Number
88A48878
Distribution Limits
Public
Copyright
Other

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