航空学报2026，Vol.47Issue(13)：60-71,12.DOI:10.7527/S1000-6893.2026.33440
高机动飞机主动流动控制环量增升设计
Design of lift augmentation via circulation of active flow control to highly maneuverable aircraft
富佳伟 1王辰 1马敏昂 1王宏 1赵彤 1刘锦通1
作者信息
- 1. 航空工业沈阳飞机设计研究所,沈阳 110035
- 折叠
摘要
Abstract
Addressing practical engineering problems related to lift augmentation during takeoff and landing to highly maneuverable aircraft,this study focuses on a thin large-sweep delta-wing with large rudder deflection.Based on the jet circulation control mechanism of active flow control,and combining both numerical simulations and wind tunnel tests for design and validation,the goal of lift augmentation via flow control for wings of large-sweep highly maneuver-able aircraft has been achieved.Flow separation occurs on both the inner flap and the outer aileron under large rudder deflection.By implementing jet control at different positions and angles,and considering engineering constraints such as bleed pressure ratio and bleed flow rate,the most optimal and feasible outer-wing jet scheme was realized.Consid-ering the complexity of parameters about active flow control,a similarity criterion study was conducted on jet control,revealing that the control effect can be uniformly evaluated using the momentum coefficient under different conditions.Based on the numerical simulation scheme,wind tunnel tests were conducted to verify the results and elucidate the relevant flow mechanisms,establishing a standardized theoretical research method and a highly feasible circulation control wing lift augmentation scheme.关键词
环量控制/柯恩达效应/流动增升/相似准则/风洞试验Key words
circulation control/Coanda effect/lift augmentation/similarity criteria/wind tunnel test分类
航空航天引用本文复制引用
富佳伟,王辰,马敏昂,王宏,赵彤,刘锦通..高机动飞机主动流动控制环量增升设计[J].航空学报,2026,47(13):60-71,12.
