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 Like XIE;Hua LIANG;Haohua ZONG;Yun WU;Yinghong Li;Zhi SU;Xuecheng LIU

作者机构：Science and Technology on Plasma Dynamics LaboratoryAir Force Engineering UniversityXi'an 710038China School of Mechanical EngineeringXi'an Jiaotong UniversityXi'an 710049China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2023年第36卷第2期

页      面：76-86页

核心收录：

学科分类：080103[工学-流体力学] 08[工学] 080104[工学-工程力学] 0801[工学-力学（可授工学、理学学位）] 

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

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

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 *** 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),*** 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),*** 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 *** lower the w/λis,the higher the wing lift coefficient will *** 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.