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Computational Analysis of Compressibility Effects on a High-Lift WingThe objective of this study was to investigate compressibility effects on a high-lift flowfield by simulating the flow about a three-dimensional multi-element wing. The computations were performed by solving both the incompressible and compressible Navier-Stokes equations (using the INS3D and OVERFLOW codes) on structured, overset grids. Turbulence was modeled via the one-equation, fully turbulent Spalart-Allmaras model. The computational results were validated with surface pressure measurements acquired at the NASA Ames 7- by 10-Foot Wind Tunnel. The geometry used for all computations consisted of an unswept wing in a landing configuration with a half-span flap and a three-quarter-span slat mounted inside a rectangular duct approximating the wind tunnel walls. The solutions were carefully examined to account for effects due to differences in algorithms. Compressibility effects were demonstrated by comparing surface particle traces, sectional pressure coefficient and boundary layer profile plots. It was found that small regions of compressibility near the slat and main-element leading edge can largely impact the flow. Even small compressibility regions can have significant global effects on the circulation and separation of each of the high-lift elements.
Document ID
20020074557
Acquisition Source
Ames Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Baker, M. David
(MCAT Inst. United States)
Nixon, David
Date Acquired
August 20, 2013
Publication Date
January 1, 1999
Subject Category
Aerodynamics
Funding Number(s)
PROJECT: RTOP 538-14-14
CONTRACT_GRANT: NAS2-14109
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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