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Progress Towards Computational Method for Circulation Control AirfoilsThe compressible Reynolds-averaged Navier-Stokes equations are solved for circulation control airfoil flows. Numerical solutions are computed with both structured and unstructured grid solvers. Several turbulence models are considered, including the Spalart-Allmaras model with and without curvature corrections, the shear stress transport model of Menter, and the k-enstrophy model. Circulation control flows with jet momentum coefficients of 0.03, 0.10, and 0.226 are considered. Comparisons are made between computed and experimental pressure distributions, velocity profiles, Reynolds stress profiles, and streamline patterns. Including curvature effects yields the closest agreement with the measured data.
Document ID
20050051580
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Swanson, R. C. (NASA Langley Research Center Hampton, VA, United States)
Rumsey, C. L. (NASA Langley Research Center Hampton, VA, United States)
Anders, S. G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2005
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA Paper 2005-0089
Report Number: AIAA Paper 2005-0089
Meeting Information
Meeting: 43rd Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 10, 2005
End Date: January 13, 2005
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.

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