Computational Analysis of Propulsion Performance of Modified Pitching Motion Airfoils in Laminar Flow

The thrust generation performance of airfoils with modified pitching motion was investigated by computational fluid dynamics (CFD) modeling two-dimensional laminar flow at Reynolds number of 10 4 . The effect of shift distance of the pitch axis outside the chord line , reduced frequency , pitching amplitude , pitching profile, and airfoil shape (airfoil thickness and camber) on the thrust generated and efficiency were studied. The results reveal that the increase in and leads to an enhancement in thrust generation and a decrease in propulsive efficiency. Besides, there exists an optimal range of for the maximum thrust and the increasing induces a rapid decrease in propulsive efficiency. Six adjustable parameters were employed to realize various nonsinusoidal pitching profiles. An increase in results in more thrust generated at the cost of decreased propulsive efficiency. The investigation of the airfoil shape effect reveals that there exists an optimal range of airfoil thickness for the best propulsion performance and that the vortex structure is strongly influenced by the airfoil thickness, while varying the camber or camber location of airfoil sections offers no benefit in thrust generation over symmetric airfoil sections.