The European High Lift Project EUROLIFT II - Objectives, Approach, and Structure

Japan Aerospace Exploration Agency Studies for the Second High-Lift Prediction Workshop

“…Compared with the experimental results, C L and C M tend to be over-predicted and under-predicted (i.e., the pitch-down moment tends to be over-predicted), respectively. The tendencies of the over-prediction and under-prediction are reasonable because the computational geometry "Config 2" for Case 1 omitted the slat and flap brackets and the existence of brackets generally increases the flow separation over the wing and flap and results in decreasing C L and increasing C M (i.e., decreasing the pitch-down moment) as discussed in [3][4][5][6][7][8][9][10][11]14]. The results on all the grids and the extrapolated grid converged solution with the SA model show higher C L and lower C M (i.e., more pitch-down moment) than those with the SST model.…”

“…Generation of computational grids with high quality around the complicated whole configurations is time-consuming and precise prediction of aerodynamic forces, such as C L max and L∕D, for the three-dimensional high-lift configurations is still a challenging task. In European high-lift projects [8][9][10], efforts to validate and improve computational fluid dynamics (CFD) technologies for the precise prediction have been conducted through the European High Lift Programs, EUROLIFT [8] and EUROLIFT II [9] and the High-lift INflight VAlidation (HINVA) project [10]. In Japan, CFD validation studies for high-lift flows have been conducted with a series of wind tunnel tests using a realistic civil aircraft configuration (Config) [3][4][5][11][12][13][14][15][16].…”

“…In the HiLiftPW-2, a series of the wing-body models of the DLR F11 in landing configuration [6,17] was used, which was representative of modern transport high-lift systems with a three-element (slat and flap) high-lift wing. The model was used for EUROLIFT I test campaigns [8,9] and the low-and high-Re test data were provided. In this paper, JAXA studies for the HiLiftPW-2 test cases including the follow-on problems using UPACS and TAS-code are summarized.…”

“…The DLR F11 model is a representative of modern transport high-lift systems with a threeelement (slat and flap) high-lift wing. The model was used for EUROLIFT I test campaigns [8,9] and the low-and high-Re test data are provided. Reference quantities of the model are listed in Table 1.…”

Integration of CFD and Wind Tunnel by Data Assimilation

“…Several higher order schemes have also been developed, and the accuracy of CFD for steady flows has become good enough for use in engineering design (1) . Recently, interest in CFD has begun to focus on unsteady flows, such as helicopter blades (2) , high-lift configuration (3) , and noise (4) . However, there are still uncertainties in CFD, such as boundary conditions, initial conditions, turbulence models, time step sizes, and grid resolution.…”