Summary of the First AIAA CFD High-Lift Prediction Workshop

Abstract

The first AIAA CFD High-Lift Prediction Workshop was held in Chicago, Illinois, in June 2010. The goals of the workshop included an assessment of the numerical prediction capability of current-generation computational fluid dynamics (CFD) technology/codes for swept, medium/high-aspect-ratio wings in landing/takeoff (high-lift) configurations. Twenty-one participants from eight countries and 18 organizations submitted a total of 39 data sets of CFD results. A variety of grid systems (both structured and unstructured) were used. Trends due to flap angle were analyzed, and effects of grid family, grid density, solver, and turbulence model were addressed. Some participants also assessed the effects of support brackets used to attach the flap and slat to the main wing. This paper analyzes the combined results from all workshop participants. Comparisons with experimental data are made. A statistical summary of the CFD results is also included.

CFD Computations for a Generic High-Lift Configuration Using TetrUSS

“…However, both models poorly predict the measured data at ST98 near wing tip, at least on the grid used for the present computations. This trend has also been observed in similar studies employing different computational methods and grids 5 . The SST model yields a stalled solution at an angle-of-attack of 34°, resulting in a large under-prediction of upper surface pressures and lift.…”

“…Present computations are based on unstructured tetrahedral grid family that is designated as the UT4 grid system 1,5 in the families of grids distributed to the HiLiftPW-1 participants. This grid system is suitable for cellcentered flow solvers.…”

“…Combined results from all participants are compared with the experimental data and statistically analyzed in Ref. 5.…”

Computational-Fluid-Dynamics Solver with Preconditioned Method for Aerodynamic Simulation of High-Lift Configuration

“…du n x dU dv n y dU dw n z dU (22) As a result, the velocity components on the boundary can be determined as…”

“…The preconditioned Lower-Upper Symmetric Gauss-Seidel (LU-SGS) implicit time-marching method is adopted to improve the convergence rate of the solution. To evaluate the stability and accuracy of the solver, flows over the two-dimensional National Aerospace Laboratory (NLR) 7301 airfoil with flap and threedimensional high-lift trap-wing configuration [19][20][21] in the First AIAA CFD High-Lift Prediction Workshop [22] are analyzed and validated by the experimental data.…”