雷诺数对涡桨飞机增升装置气动特性影响的计算研究  

Numerical Investigation of Reynolds Number Effects on Aerodynamics Characteristics of High Lift System for Turboprop Aircraft

作　　者：许瑞飞[1] 钱瑞战[1] 雷武涛[1] 

机构地区：[1]中国航空工业集团公司第一飞机设计研究院,西安710089

出　　处：《航空工程进展》2016年第4期420-425,共6页Advances in Aeronautical Science and Engineering

基　　金：航空科学基金(20143203002)

摘　　要：雷诺数是表征流体粘性对流动影响的相似参数,对飞机部件的气动性能具有重要的影响。利用商业软件CFX对某民用涡桨飞机增升装置构型进行变雷诺数计算研究,详细分析雷诺数对升力系数、失速特性以及附面层速度特性的影响。结果表明:雷诺数对最大升力系数和失速迎角都有显著的影响;不同雷诺数下机翼分离形态变化显著,大雷诺数下机翼分离区域较小;不同雷诺数下机翼附面层状态不一致,雷诺数增大使得附面层速度型更饱满,机翼的抗分离能力增强。Reynolds number is one of the most useful similarity parameters in fluid dynamics which denotes the effect of the viscosity on the fluid flow. It has an important effect on the aerodynamic characteristic of the air- craft. The variable Reynolds number research of the high lift for one of the civil turboprop aircraft is completed by the commercial software CFX. The effect of Reynolds number on the lift coefficient, stall characteristic, and the velocity characteristic of the boundary layer are also analyzed in detail. The research indicates that the Reyn- olds number has the notable effect on the maximum lift coefficient and the stall angle. The state of the flow sep- aration on the wing is changed obviously under the different Reynolds number. The area of the separation be- comes smaller when the Reynolds number is increased. The state of the boundary layer is different under the different Reynolds number. When the Reynolds number increases, the velocity profile is fuller, and the trend of separation is limited.

关 键 词：涡桨飞机 增升装置 雷诺数 气动特性 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]