Convolution Kernels for a NACA 0012 Airfoil Based on Unsteady Pressure Wind Tunnel Measurements

The unsteady pressure distribution over a NACA 0012 air foil is measured in a low-speed wind tunnel for a rigid airfoil and control surface configuration. The experimental protocol is to give a step change in the airfoil angle of attack and the control surface deflection angle to capture the time history of the flow given this excitation. The data is then used to compute the kernel functions for a Reduced-Order Modeling (ROM) of an aero elastic system using experimental data instead of computational results. The method will be validated by implementing the experimental kernels to reconstruct the measured oscillatory airfoil pressure distribution.

Duke Scholars

Author Earl H. Dowell Thomas Lord Department of Mechanical Engineering and Materia ...