Computations of High-Lift Wing Configuration on Unstructured Grids Using k-ω Models
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Turbulent flow computations of the NASA "trap-wing" high-lift configuration are performed at various angles of attack usinga k-ωfamily ofmodels to assess their capabilities for high-lift design and optimization applications. The four k-ωmodel variants used are: 1)Wilcox's 1988 baseline model; 2) variable-β* model consistentwith the rapidly strained limit; 3) variable-β* model consistent with the explicit algebraic Reynolds stress model; and 4) Wilcox's 2006 enhanced model. Subject to the conditions of this test, the variable-β* model consistent with the rapidly strained limit not only performs the best but is also numericallymore robust and does not require the use of a production-to- dissipation limiter. Overall, our findings indicate that variable β* makes an important difference. In the proximity of stall, a low-Reynoldsnumber correction to eddy viscosity may be needed to accurately capture experimental behavior. The results provide much needed insight into the models' predictive capabilities and identify areas for future k-ω model improvements. © 2012 AIAA.
author list (cited authors)
Reyes, D. A., Girimaji, S. S., Pandya, M. J., & Abdol-Hamid, K. S.