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.
出处
《航空科学技术》
2013年第4期26-30,共5页
Aeronautical Science & Technology
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
high lift system
turboprop aircraft
integration
multi-element airfoil
aerodynamic design
wind tunnel test
performance
