基于襟/缝翼吹气技术的短距起降飞行器增升策略的数值模拟研究  

The Numerical Simulation Research on High Lift Enhancement Strategies of STOL Aircraft Based on Flap and Slat Blowing

作　　者：郝璇[1] 刘芳[1] 王斌[1] 

机构地区：[1]中国航天空气动力技术研究院第二研究所,北京100074

出　　处：《航空工程进展》2016年第4期408-419,共12页Advances in Aeronautical Science and Engineering

摘　　要：边界层吹气是增加飞行器升力的有效措施。针对普通陆基起降飞行器,根据总体参数对其实现舰载起降的气动力特性需求进行分析并提出五组初步方案;同时对襟/缝翼定常吹气的增升潜力进行数值模拟研究。结果表明:襟/缝翼吹气能够使升力系数显著增加;襟翼和缝翼吹气存在相互干扰,升力增量的变化率随吹气动量系数的增加而减小;当吹气动量系数不大于6%时,襟/缝翼吹气最大升力系数最大可达1.85左右,α=15°时升力系数最大可达1.40左右,可满足所提五组气动力特性需求方案中的三组方案的舰载起降需求。The boundary layer blowing is an effective measure to increase the lift of flight vehicles. For a common flight vehicle designed for on land taking off and landing, the aerodynamie characteristic requirements are analyzed to realize its on-deck taking off and landing based on the project parameters, and five schemes are proposed. The lift increase potential of flap and slat steady blowing is researched by numerical simulation. The results indicate that the flap and slat blowing can enhance the lift observably, whereas some interference will appear when both the flap and slat blowing, which lead the slope of increased lift declining as the blowing momen- tum coefficient increasing. When the blowing momentum coefficient less than 6%, the maximum lift coefficient can reach about 1.85 and the lift coefficient at 15% of the angle of attack with both the flap and slat blowing can reach about 1.40. The aerodynamic characteristic requirements can be satisfied for taking off and landing on the deck in three of the five schemes.

关 键 词：短距起降 高升力装置 定常吹气 襟翼 缝翼 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]