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Study of the Effect of Two-Dimensional Cavities on the Boundary Layer in an Adverse Pressure GradientOne concept for high lift aerodynamics is the trapped-vortex. Recently it has been suggested that several spoilers located at different chordwise locations on an airfoil could be deployed to form several cavities in the chordwise direction. This may provide a means of increasing upper surface camber and thereby increase wing lift. It is envisioned that the cavities would be located on an airfoil in its pressure recovery region. Investigations of the effect of one or more cavities on the adjacent boundary layer in an adverse boundary layer were not found in a literature survey. Since flow separation can be caused by flow over cavities, boundary layer measurements were made in the vicinity of cavities which were located in an adverse pressure gradient to study the associated flow in an effort to identify any benefits. The experimental data from the present investigation indicate a minimal impact on the boundary layer profiles is caused by the presence of cavities in either a constant pressure freestream or an adverse pressure gradient. The data from the experimental investigation has been obtained and analyzed. The computational investigation using an incompressible Navier-Stokes code show that reasonable results are being obtained when they are compared with the experimental data.
Document ID
20020027465
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Margason, Richard J.
(NASA Ames Research Center Moffett Field, CA United States)
Platzer, Max F.
(Naval Postgraduate School Monterey, CA United States)
Olson, Lawrence E.
Date Acquired
August 20, 2013
Publication Date
January 1, 1995
Subject Category
Fluid Mechanics And Thermodynamics
Meeting Information
Meeting: 34th Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 15, 1996
End Date: January 18, 1996
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 505-59-53
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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