Turbulent flow computations of the NASA “trap-wing” high-lift configuration are performed at various angles of attack using a family of models to assess their capabilities for high-lift design and optimization applications. The four model variants used are: 1) Wilcox’s 1988 baseline model; 2) variable- model consistent with 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 numerically more 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-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 model improvements.
Computations of High-Lift Wing Configuration on Unstructured Grids Using Models
Journal of Aircraft ; 50 , 6 ; 1682-1695
2013-10-16
14 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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