%0 Journal Article
%T Reduced
%A Haotian Gao
%A Jason Tran
%A Jayant Sirohi
%A Mingjun Wei
%J International Journal of Micro Air Vehicles
%@ 1756-8307
%D 2018
%R 10.1177/1756829317708318
%X This paper describes a methodology to predict the loads generated by a flexible flapping wing. The three-dimensional, whole field wing deformation was first measured using a non-contact optical technique. The measured deformation and motion were then input to a reduced-order model of the flapping wing to calculate the loads generated. Experiments were performed on a thin rectangular plate of 100£¿mm wing length flapping in air at a frequency of 15£¿Hz and stroke amplitude of 40¡ã. The wing deformation as well as wing root loads were measured and showed good agreement with previously published data. A direct numerical simulation of the Navier¨CStokes equation with exactly the same configuration, but at lower Reynolds number, provided full-field dataset for the development of data-driven reduced-order models. A modified proper orthogonal decomposition-Galerkin method, which includes extra terms to represent moving boundaries, was applied for reduced-order model development. It was found that the reduced-order model with only eight proper orthogonal decomposition modes was sufficient to show good correlation of loads with direct numerical simulations and experimentally measured trends
%K Flapping wing
%K reduced order model
%K wing deformation
%K load sensing
%K flexible wing
%U https://journals.sagepub.com/doi/full/10.1177/1756829317708318