涡桨飞机短舱/增升装置一体化气动设计研究  

Aerodynamic Design and Research of Integral Nacelles and High Lift System for Turboprop Aircraft

作　　者：王银虎[1] 段卓毅[1] 雷武涛[1] 

机构地区：[1]中航工业第一飞机设计研究院

出　　处：《航空科学技术》2013年第4期26-30,共5页Aeronautical Science & Technology

摘　　要：对涡桨飞机增升装置设计的特殊性进行了分析,指出了传统增升装置设计方法在涡桨飞机增升装置设计上存在的问题。详细描述了涡桨飞机短舱/增升装置一体化气动设计方法的流程,并对某涡桨飞机的多段翼型参数优化设计、短舱/三维增升装置一体化设计及风洞试验结果进行了简要介绍。相对于传统的增升装置设计方法,采用涡桨飞机短舱/增升装置一体化气动设计方法显著提高了涡桨飞机起飞、着陆构型的气动性能。The particularity of high lift system design for turboprop aircraft is analyzed. Some problems are pointed out when traditional high lift system design methodology is used to design the high lift system for turboprop aircraft. The design process of integral nacelles and high lift system is described in detail. A test case of a turboprop aircraft design is investigated, including three parts： the parametric optimization of multi-element airfoils, the optimization of integral nacelles and high lift system and the wind tunnel tests of the optimized turboprop aircraft. Compared with the traditional design methodology, the design using this new design methodology improves the takeoff and landing performance of turboprop aircraft dramatically.

关 键 词：增升装置 涡桨飞机 一体化 多段翼型 气动设计 风洞试验 性能 

分 类 号：V228.5[航空宇航科学与技术—飞行器设计]