1. Prediction 01` the 2-D. high-lift flow field is still unreliable despite recent advances in the computational field. A joint NASA - Boeing workshop was held in 1996 to àddress issues related to accuracy of CFD high-lift predictions. A research program was laid out in order to address both the effect of transition location and turbulence model on the accuracy of the computational predictions. One of the findings was that transition location and code implcmcntation played a key role in accurately predicting the flow-field'.
2. AIAA-2000-0139
3. over the model blowing tubes wcrc positioned tangentially at approximately 15% 01`the flap chord and connected to shop air regulated at 80 psi. Spanwise prcssurc measurements made near the trailing edges of both the main element and flap confirm that 2-D flow was achieved (figure 3). The worst case scenario (c(= IO") has been shown in figure 3. Pressure measurements were made using an ESP system accurate to +/- 0.045% of full scale. Once 2-D llow was achieved. smoke flow visualization was performed Z/S IO ensure that the model was not inducing tunnel lloor Figure 3. Confirmation of 2-D tlow from spanwise or ceiling boundary layer separation. Oil Ilow (titanium pressure measuremcnls at 0! = IO0022.