As a portion of the Benchmark Models Program at NASA Langley (Ref I), three models with the same rectangular plankton, but with different airfoils were flutter tested on the Pitch and Plunge Apparatus (PAPA. Ref 2-3). These models were designed and tested to provide flutter data for evaluating Computational Aeroelasticity (CA) programs with emphasis on transonic flows The geometry of the wings was kept simple to reduce the complexity of the geometry processing for computation and in the interpretation of the results. One model was built with the NACA 0012 airfoil culled the B0012, one with the NACA 64A0lC airfoil called the B64AOlO. and one with an NASA SC(2)-0414 airfoil called BSCW. These airfoils, shown in Fig I, were not selected to provide a systematic empirical trend study of thickness or airfoil type, hut to provide flutter data for wings with different transonic airfoil characteristics. The NACA 0012 airfoil has a forward loading and for transonic flows, a shock long initially ahead of midchord. The NACA 64A010 airfoil has a more mild evolution of the shock which forms initially near midchord. The NASA SC(2)-0414 has a strong aft loading and the associated low oft upper surface. There was considerable experience in two dimensions with the NACA 0012 and 64A01C airfoils based on comparisons with the early two- dimensional unsteady aerodynamic data of Ref 4. The supercritical airfoil (Ref I) was chosen as a relatively modem airfoil for comparison.
Test Cases for Flutter of the Benchmark Models Rectangular Wings on the Pitch and Plunge Apparatus
2000
28 pages
Report
No indication
English
A DEMONSTRATION OF PITCH-PLUNGE FLUTTER SUPPRESSION USING LQG CONTROL
British Library Conference Proceedings | 2010
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