Numerical study of the influence of spoiler deflection on high-lift configuration  

作　　者：Wenhu Wang Peiqing Liu 

机构地区：[1]School of Aeronautic Science and Engineering, Beihang University, Beijing, China

出　　处：《Theoretical & Applied Mechanics Letters》2017年第3期159-163,共5页力学快报（英文版）

摘　　要：This paper numerically studies the influence of the downward spoiler deflection on the boundary layer flow of a high-lift two-element airfoil consisting of a droop nose, a main wing, a downward deflecting spoiler and a single slotted flap. Both of the boundary layer of the upper surface of the spoiler and the confluent boundary layer of the upper surface of the flap become thicker, as the downward spoiler deflection increases. Compared to the attached flow at the angle of attack of 10°, the flow of the upper surface of the spoiler becomes separated at the angle of attack of 16° when the spoiler deflection is large enough, which corresponds to the boundary layer flow reversal in velocity profiles.This paper numerically studies the influence of the downward spoiler deflection on the boundary layer flow of a high-lift two-element airfoil consisting of a droop nose, a main wing, a downward deflecting spoiler and a single slotted flap. Both of the boundary layer of the upper surface of the spoiler and the confluent boundary layer of the upper surface of the flap become thicker, as the downward spoiler deflection increases. Compared to the attached flow at the angle of attack of 10°, the flow of the upper surface of the spoiler becomes separated at the angle of attack of 16° when the spoiler deflection is large enough, which corresponds to the boundary layer flow reversal in velocity profiles.

关 键 词：HIGH-LIFT SPOILER Boundary layer Numerical simulation 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]