摘要
小型通用飞机通常需要采用相对简单的增升系统及自身良好的气动性能以满足起飞和着陆阶段的安全和效益的匹配要求,这些与大迎角空气动力学特性有关。而控制翼身结合部的流动分离,对改善小型飞机的大迎角性能具有重要的工程应用价值。通过数值模拟的方法,对某一典型通用飞机外形的着陆构型的气动性能及翼根处的流动机理研究得出,翼根处产生的马蹄涡及边角涡以及根部前缘吸力峰增高是导致翼根气流分离的主要原因,由此可通过前缘整流、展向整流和中后段三方面进行相关的整流方案设计。
The general aircraft need have simple High Lift system and good aerodynamic performance to meet the safety and efficiency matching requirements during takeoff and landing stages, which are related to the aerodynamic characteristics at high angles of attack. Controlling the flow separation at the Wing-fuselage junction has important engineering application value for improving the high angle of attack performance of small aircraft. Through the numerical simulation, the aerodynamic performance and the flow mechanism at the wing root of a typical general aircraft are studied. It is concluded that the horseshoe vortices,corner vortices at the wing root and the increase of the suction peak at the leading edge of the wing root aircraft are the main reasons for the separation of the wing root airflow. Therefore, the design of rectification schemes can be carried out from three aspects: front rectification, spread rectification and mid-rear rectification.
作者
叶露
YE Lu(Flight Technology College,Civil Aviation Flight University of China,Guanghan,Sichuan 618307)
出处
《液压与气动》
北大核心
2019年第11期32-36,共5页
Chinese Hydraulics & Pneumatics
基金
国家自然科学基金民航联合项目(U1733127)
中国民用航空飞行学院青年基金(Q2019-024)
关键词
通用飞机
翼根气动特性
流动机理
翼根整流方案
general aircraft
aerodynamic performance of wing root
flow mechanism
wing-body junction surface design method
