超临界机翼飞行验证机的增升装置设计  

High Lift System Design for a Supercritical Wing Flight Test Plane

作　　者：钱瑞战[1] 段卓毅[2] 付大卫[2] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083 [2]中航第一飞机设计研究院气动设计研究室

出　　处：《飞行力学》2006年第2期86-88,92,共4页Flight Dynamics

摘　　要：为进行超临界机翼气动设计技术的飞行验证,将某教练机改装为飞行验证机,为此必须进行增升装置的重新设计。在保持原型机襟翼平面参数和运动机构不变的条件下,完成了验证机增升装置的气动力设计工作。风洞试验表明,改装成功的验证机增升装置具有良好的气动特性。In order to validate the philosophy and software of supercritical wing design, a training plane is refitted and its high lift system is redesigned. This paper presents the procedure and results of the high lift system design. The planar parameters and the mechanism of the flap of the training plane are retained, which is of great importance in this research project. Wind tunnel tests indicate that the designed high lift system has good aerodynamics characteristics.

关 键 词：超临界机翼 飞行试验 增升装置 风洞试验 气动特性 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]