VALIDATION STUDY OF CFD ANALYSIS FOR HIGH-LIFT SYSTEMS

In this study, three-dimensional flow computations around a simplified three-element high-lift configuration and a realistic high-lift configuration with a nacelle-pylon are performed. By comparison with the results, problems associated with the realistic configuration are clarified and the ways to improve the reliability of CFD methods are discussed in simulating the flows around highlift devices. The simplified three-element trapezoidal wing model tested at NASA Langley and Ames is computed using both multi-block structured and unstructured mesh method and the mesh dependency is discussed. Importance of the mesh resolution to resolve the separated corner flows near the wing-fuselage junction is shown to improve the accuracy of computational results. Computations of the realistic configuration model tested at JAXA are performed using the unstructured mesh method and compared with the experimental data. Influences by the turbulent transition of the boundary layer and the presence of the nacellepylon on the aerodynamic forces are discussed.

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