Improving aircraft aerodynamic performance with bionic wing obtained by ice shape modulation  

作　　者：Like XIE Hua LIANG Haohua ZONG Yun WU Yinghong LI Zhi SU Xuecheng LIU 

机构地区：[1]Science and Technology on Plasma Dynamics Laboratory,Air Force Engineering University,Xi'an 710038,China [2]School of Mechanical Engineering,Xi'an Jiaotong University,Xi'an 710049,China

出　　处：《Chinese Journal of Aeronautics》2023年第2期76-86,共11页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China(No.12002384);the National Key Laboratory Foundation of China(No.614220210200112)。

摘　　要：For Unmanned Aerial Vehicles(UAVs)with limited electrical power to achieve effectively anti-/de-icing at the leading edge of the wing,a strategy of ice shape modulation was proposed.Isolated simulated ice shape pieces printed by 3D printing technology are mounted on a NACA0012 finite wing model,and its lift/drag coefficients and suction-side velocity fields are measured by the six-component force balance and the Particle Imaging Velocimetry(PIV),respectively.The ratio of the spanwise length of a single ice shape piece to chord length and the spanwise length of the non-icing area between the two adjacent single ice shape pieces are defined as dimensionless ice shape length(w/c)and dimensionless modulation ratio(w/λ),respectively.The results indicate that for a fixed w/λ,the wing lift coefficient first increases and then drops with increasing w/c,and a peak value exists when w/c is between 0.1 and 0.2.The lower the w/λis,the higher the wing lift coefficient will be.The periodical variation of the flow separation area along the spanwise direction is attributed on the one hand to the acceleration effect of the flow field in the non-icing area which reduces the separation area,and on the other hand to the cross-flow caused by the streamwise vortices from the non-icing area to the icing area which promotes the mixing of the flow field(similar to vortex generators).The obtained modulation law is verified through flight tests and provides guidance for the use of ice shape modulation scheme for UAVs that cannot be completely anti-/deicing under severe weather conditions.

关 键 词：Dimensionless ice shape length Dimensionless modulation ratio Ice shape modulation NACA0012 finite wing Particle imaging velocimetry(PIV) Unmanned aerial vehicles(UAVs) 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]