The flow over two different multielement airfoil configurations is com
puted using linear eddy-viscosity turbulence models and a nonlinear ex
plicit algebraic stress model. Transition locations that were recently
measured using hot film on one of the configurations are presented, a
nd the effect of transition location on the computed solutions is expl
ored. Deficiencies in make profile computations are found to be attrib
utable in large part to poor boundary-layer prediction on the generati
ng element rather than on inadequate turbulence modeling in the wake.
Using measured transition locations for the main element improves the
prediction of the main-element boundary-layer thickness, skin friction
, and wake profile shape. However, using measured transition locations
on the slat still yields poor slat-wake predictions. The computation
of the slat flowfield remains a major problem in the successful predic
tion of multielement flows. In general, the nonlinear, explicit algebr
aic stress turbulence model yields results that are similar to those o
f the linear eddy-viscosity models.