航空科学技术Issue(4)：26-30,5.
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
摘要
Abstract
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 nacel es 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 nacel es 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 dramatical y.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Key words
high lift system/turboprop aircraft/integration/multi-element airfoil/aerodynamic design/wind tunnel test/performance引用本文复制引用
王银虎,段卓毅,雷武涛..涡桨飞机短舱/增升装置一体化气动设计研究[J].航空科学技术,2013,(4):26-30,5.
