Computations of High-Lift Wing Configuration on Unstructured Grids Using

• Published in: Journal of aircraft 2013-11, Vol.50 (6), p.1682-1695
• Main Authors: Reyes, Dasia A, Girimaji, Sharath S, Pandya, Mohagna J, Abdol-Hamid, Khaled S
• Format: Article
• Language: English
• ISSN: 0021-8669; 1533-3868
• DOI: 10.2514/1.C031492

Turbulent flow computations of the NASA “trap-wing” high-lift configuration are performed at various angles of attack using a k-ω family of models to assess their capabilities for high-lift design and optimization applications. The four k-ω model variants used are: 1) Wilcox’s 1988 baseline model; 2) variable-β* model consistent with 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 numerically more 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-Reynolds-number 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.