Characterization of Aerodynamic Forces on Wings in Plunge Maneuvers

Thumbnail Image
Publication date
Defense date
Journal Title
Journal ISSN
Volume Title
American Institute of Aeronautics and Astronautics
Google Scholar
Research Projects
Organizational Units
Journal Issue
We present experiments and simulations of plunging maneuvers of large amplitude, for velocity ratios of G=1 and 2, defined as the ratio between the peak plunge velocity and the freestream velocity. We explore the effect of the airfoil shape by considering a NACA 0012 wing and a flat plate. The experiments are performed with wings with aspect ratios of 4 and 4.86, whereas the simulations are performed using a model of an infinite-aspect-ratio wing. We report the time evolution of the force coefficients and flow visualizations. A good qualitative agreement is found between experiments and simulations, with small discrepancies in the maximum and minimum lift coefficients observed during the maneuvers and somewhat larger discrepancies during the postmaneuver phase. It is found that the airfoil shape has a small effect on the lift coefficient but a somewhat larger effect on the drag coefficient. We also perform a force decomposition analysis to relate vortical structures to the force on the wings, providing a quantitative measurement of the effect of the leading-edge vortex and trailing-edge vortex on the peak aerodynamic forces.
Freestream velocity, Symmetric airfoil, Trailing edges, Flow visualization, Aspect ratio, Vortex breakdown, Lift coefficient, Direct numerical simulation, Incompressible flow, Wing configurations
Bibliographic citation
AIAA Journal, (2021), 59(2), pp. 736-747.