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

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

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 aerodynamic characteristic requirements to on-deck taking off and landing were analyzed based on the project parameters and five schemes were proposed. The lift increase potential of flap and slat steady blowing was 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 slop of lift increase decrease as the blowing moment coefficient augment. When the blowing moment 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, from which three schemes can be satisfied for taking off and landing on the deck.