Numerical and Experimental Analysis of Purely Pitching and Purely Plunging Airfoils in Hover

2012-07-06
Hızlı, Hasan
Kurtuluş, Dilek Funda
Numerical and experimental study of two-dimensional purely pitching and purely plunging SD7003 and NACA0012 airfoil sections in hover mode is presented. Main objectives of the study are to provide a better understanding of the aerodynamic phenomena and the vortex topology of flapping wings for application to micro air vehicle (MAV) designs and to compare numerical and experimental results for observing the performance of the experimental setup for future applications. The commercial CFD package program Fluent 6.3 is used for the numerical simulation of the flow whereas the instantaneous velocity field data of the flow is collected by Particle Image Velocimetry (PIV) measurements. Among the current studied cases, the highest mean lift coefficient is obtained from purely plunging NACA0012 airfoil section while the lowest is obtained from purely pitching NACA0012 airfoil section. Moreover, purely plunging SD7003 airfoil section gives the lowest mean drag coefficient whereas purely pitching SD7003 airfoil section gives the highest. In a following work, a comprehensive experimental visualization will be performed with time resolved PIV (TR-PIV) measurements.
Citation Formats
H. Hızlı and D. F. Kurtuluş, “Numerical and Experimental Analysis of Purely Pitching and Purely Plunging Airfoils in Hover,” 2012, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/76730.