TY - JOUR
T1 - Numerical Investigations on Aerodynamic Forces of Deformable Foils in Hovering Motions
AU - Zhao, Yong
AU - Yin, Zhen
AU - Su, Xiaohui
AU - Zhang, Jiantao
AU - Cao, Yuanwei
N1 - Funding Information:
This research is supported by The National Natural Science Foundation of China (NNSFC), project No: 11672059. The financial support from NNSFC is gratefully acknowledged. Financial support from the DUT Haitian Scholars program is also acknowledged.
PY - 2017/9/8
Y1 - 2017/9/8
N2 - The aerodynamic effects of wing deformation for hover flight are numerically investigated by a two-dimensional finite-volume (FV) Arbitrary Langrangian Eulerian (ALE) Navier-Stokes solver. Two deformation models are employed to study these effects in this paper, which are a full deformation model and a partial deformation one. Attentions are paid to the generation and development of leading edge vortex (LEV) and trailing edge vortex (TEV) which may illustrate the differences of lift force generation mechanisms from those of rigid wings. Moreover, lift coefficient Cl, drag coefficient Cd, and figure of merit, as well as energy consumption in hovering motion for different deformation foil models, are also studied. The results show that the deformed amplitude, 0.1∗chord, among the cases simulated is an optimized camber amplitude for full deformation. The results obtained from the partial deformation foil model show that both Cl and Cd decrease with the increase of camber amplitude. It is found that the effect of deformation in the partial deformation model does not enhance lift force due to unfavorable camber. But TEV is significantly changed by the local AOA due to the deformation of the foil. Introduction.
AB - The aerodynamic effects of wing deformation for hover flight are numerically investigated by a two-dimensional finite-volume (FV) Arbitrary Langrangian Eulerian (ALE) Navier-Stokes solver. Two deformation models are employed to study these effects in this paper, which are a full deformation model and a partial deformation one. Attentions are paid to the generation and development of leading edge vortex (LEV) and trailing edge vortex (TEV) which may illustrate the differences of lift force generation mechanisms from those of rigid wings. Moreover, lift coefficient Cl, drag coefficient Cd, and figure of merit, as well as energy consumption in hovering motion for different deformation foil models, are also studied. The results show that the deformed amplitude, 0.1∗chord, among the cases simulated is an optimized camber amplitude for full deformation. The results obtained from the partial deformation foil model show that both Cl and Cd decrease with the increase of camber amplitude. It is found that the effect of deformation in the partial deformation model does not enhance lift force due to unfavorable camber. But TEV is significantly changed by the local AOA due to the deformation of the foil. Introduction.
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U2 - 10.1088/1757-899X/234/1/012006
DO - 10.1088/1757-899X/234/1/012006
M3 - Conference article
AN - SCOPUS:85033684882
SN - 1757-8981
VL - 234
JO - IOP Conference Series: Materials Science and Engineering
JF - IOP Conference Series: Materials Science and Engineering
IS - 1
M1 - 012006
T2 - 2017 International Conference on Advanced Technologies in Design, Mechanical and Aeronautical Engineering, ATDMAE 2017
Y2 - 12 July 2017 through 14 July 2017
ER -