Computations of High-Lift Wing Configuration on Unstructured Grids Using k- Models Conference Paper uri icon


  • Turbulent flow computations of the NASA "trap-wing" high-lift configuration are performed at various angles of attack usinga k-family ofmodels to assess their capabilities for high-lift design and optimization applications. The four k-model variants used are: 1)Wilcox's 1988 baseline model; 2) variable-* model consistentwith the rapidly strained limit; 3) variable-* 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-* 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 * 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- model improvements. 2012 AIAA.

published proceedings

  • Journal of Aircraft

author list (cited authors)

  • Reyes, D. A., Girimaji, S. S., Pandya, M. J., & Abdol-Hamid, K. S.

citation count

  • 0

complete list of authors

  • Reyes, Dasia A||Girimaji, Sharath S||Pandya, Mohagna J||Abdol-Hamid, Khaled S

publication date

  • November 2013