Effects of flexibility on the hovering performance of flapping wings with different shapes and aspect ratios

The effects of isotropic homogeneous flexibility on the aerodynamic performance of flapping wings with different shapes and aspect ratios in hover at a Reynolds number of 400 have been studied numerically with a 3-D Navier-Stokes solver coupled with a structure solver. Three wing shapes, defined by the radius of the first moment of wing area, (r) over bar (1) (=0.43, 0.53 and 0.63), with four aspect ratios, AR (=1.5, 2.96, 4.5 and 6.0) are considered. We used a set of moderately flexible wings with an effective stiffness of 14 and 2.31 (for the mass ratio, m* = 4.0 and 0.66 respectively) and a set of more flexible wings with an effective stiffness of 6.12 and 1.01 (for m* = 4.0 and 0.66 respectively). The wings have a limited spanwise twist and a dominant chordwise flexibility because the leading edge is modeled as rigid. The results show that although the prescribed kinematics is advanced pitch rotation, it becomes symmetric or delayed pitch rotation depending on the value of (r) over bar (1), the degree of flexibility and the mass ratio. This change in pitch angle kinematics causes variations in the time histories of lift and power with flexibility including the timings and magnitudes of lift and power peaks. Flexible wings with high AR such as 4.5 and 6.0 produce less lift than rigid wings for both mass ratios because of lower pitch angles during the mid-stroke, but they are more efficient in terms of power economy; for example, 11% less lift but 33% higher power economy at AR = 6.0, = 0.63 and m* = 0.66. At m* = 4.0, the low (r) over bar (1) and high AR wings maximize PE for a given lift. However, at m* = 0.66, there is a limited range of lift for which low (r) over bar (1) and high AR wings are efficient, as (r) over bar (1)= 0.63 wing at higher AR (=6.0) consumes lesser aerodynamic power than (r) over bar (1) = 0.43 and 0.53 wings by flapping at a lower pitch angle; therefore, the PE of low (r) over bar (1) (=0.43 and 0.53) may drop below (r) over bar (1) = 0.63 wing for a given lift. (C) 2018 Elsevier Ltd. All rights reserved.