大型水陆两栖飞机吹气襟翼设计与分析验证

针对大型水陆两栖飞机的使用特点和指标要求,以原型机翼为基础,重点开展机翼附面层控制增升装置设计技术研究,设计了附面层控制的吹气襟翼方案.采用计算流体动力学方法作为初步设计的评估手段,全面分析评估了设计方案的气动力特性和流场结构,最后通过风洞试验验证了该方案的增升效果.结果显示该设计方案在较宽的吹气动量系数范围内,最大升力系数均有不同程度的增幅,在吹气动量系数约为0.2左右时,获得最大的升力系数增量约为1.0,按照原型机的滑流影响规律推算,当采用吹气襟翼的主动流动控制方案后,起降速度能下降约30%,达到了设计指标. 

Design and test of a jet flap for a large amphibian

According to the requirements of a large amphibian''s operating features and performance based on the original wing, a high-lift device design technology of boundary layer control jet flap was studied.The scheme of boundary layer control jet flap was designed. By using computational fluid dynamics numerical simulation as a means to assess the preliminary design, the design scheme''s aerodynamic characteristics and flow field structure were analysed and evaluated, and finally wind tunnel tests were conducted to verify the lift effect of the scheme.The result of the design scheme showed that in a wide range of blowing momentum coefficient, the maximum lift coefficient had varying degrees of growth; when the blowing momentum coefficient was 0.2, the incremental maximum lift coefficient was 1.0; according to the influence of the prototype slipstream projections, when the boundary layer control jet flap was employed, the take off and landing speed could drop about 30%, achieving the design target.