2Dunsteadycomputationswithdeformationandadaptation.pptVIP

Vortragstitel 2D unsteady computations with deformation and adaptation for COSDYNA Tony Gardner DLR AS-HK Summary Overview of project COSDYNA Computational geometry TAU deformation module Adaptation scheme Example computations and initial results Conclusion Show Video 1 (Example of method) HighPerFlex DLR internal High Performance Flexible Aircraft project (HighPerFlex) 2003-2006 LAWIA – (Last- und Widerstandsabminderung) Load and drag reduction on a full A340 model by the steady CFD investigation of TED settings on an aeroelastically coupled aircraft. COSDYNA – (Control surface dynamics) Numerical and experimental investigation of unsteady profile and TED oscillations JENIFA – (Jet engine interference in flutter analysis) Experimental and numerical work to compliment the DLR-ONERA project WIONA (wing with oscillating nacelle) COSDYNA unsteady computations To compute unsteady coefficients for comparison with TWG experiments in October 2006 TWG experiments will be performed with a 2D VC-Opt airfoil in the adaptive test section. Forced oscillations of flap and airfoil can be programmed or the airfoil can swing freely. Computations must be at least partially performed beforehand due to time constraints. Computations must include flap and airfoil movement. Optimally, computations will not include gap flow Computations include cases with strong shocks, and thus will optimally allow adaptation 2D VC-Opt airfoil in TWG Geometry VC-Opt, length 300mm Design Mach =0.775 With 25% flap (gapless) deployed by grid deformation Re=2 million 2D CENTAUR grid Farfield at r=50 chords (needs farfield vortex correction) Surface points at 2mm spacing 28 structured sublayers (no cell chopping) Built for y+=1 Raw grid has 50,000 points before 2D reduction Flap movement Chimera Requires a gap between body and flap (non-physical) Gapless using automatic hole cutting is in development Deformation Can perform gapless movement Requires definition of the new surface position Han