Aerodynamic improvement of a delta wing in combination with leading edge flaps

作     者：Tadateru Ishide Mao Itazawa 

作者机构：National Institute of TechnologyKisarazu College2-1 1-1 Kiyomidai-higashiKisarazu CityChiba292-O041Japan 

出 版 物：《Theoretical & Applied Mechanics Letters》 (力学快报（英文版）)

年 卷 期：2017年第7卷第6期

页      面：357-361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）] 

主　　题：Delta wing Leading edge flap PIV analysis Leading edge vortex Aerodynamic characteristics 

摘      要：Recently, various studies of micro air vehicle （MAV） and unmanned air vehicle （UAV） have been reported from wide range points of view. The aim of this study is to research the aerodynamic improvement of delta wing in low Reynold＇s number region to develop an applicative these air vehicle. As an attractive tool in delta wing, leading edge flap （LEF） is employed to directly modify the strength and structure of vortices originating from the separation point along the leading edge. Various configurations of LEF such as drooping apex flap and upward deflected flap are used in combination to enhance the aerodynamic characteristics in the delta wing. The fluid force measurement by six component toad ceil and particle image velocimetry （PIV） analysis are performed as the experimental method. The relations between the aerodynamic superiority and the vortex behavior around the models are demonstrated.