一种新型商用飞机翼梢小翼设计及优化  

Design and Optimization of Winglet for a New Type Commercial Aircraft

作　　者：杜绵银[1] 崔尔杰[1] 陈培[1] 苏诚[1] 

机构地区：[1]航天空气动力技术研究院,北京100074

出　　处：《飞机设计》2012年第2期23-27,31,共6页Aircraft Design

摘　　要：翼梢小翼可以有效的减小耗散飞机的翼尖涡,减小诱导阻力,从而达到商用飞机减阻增升、节省燃油的目的。本文研究分析了blended winglet和raked wingtip两类小翼的特点,设计了综合这两类小翼特性的翼梢小翼,具有结构简单,增加的有效翼展小、适合于中小型机场特点。同时研究了bladed wingtip形式翼梢小翼的设计原理、设计方法及流场特性。采用的外形参数化设计及自动生成程序方法通过小翼的前后缘来确定小翼的几何形状,具有快速生成外形、易实现优化设计、工程设计效率高等特点。本文设计的bladed wingtip形式的翼梢小翼具有设计点压力峰值低、没有激波、翼尖不易先分离、在增加的有效展长很小的情况下仍有较好的减阻效果等特点。The effect of winglet that has been widely used on commercial aircraft as a means of enhancing fuel efficiency is to reduce the induced drag caused by wing tip vortex.This report presents a new type winglet,bladed wingtip designed as a mixture of blended winglet and raked wing tip,after the character analysis of both blended winglet and raked wing tip.The bladed wing-tip with its simple configures and limited increased wing span is fit to the commercial aircraft landed on the small and medium airport.Also this report presents the design principle,the design method,and aerodynamic characters of the winglet.The design method,parameterized design and automatic building process of winglet shape,has the advantages of rapidly shape building,the realizable optimization design and the high efficiency of engineering design.As a result,the winglet designed in this report has such characters as low pressure coefficient peak value,no shock wave at winglet design point,the flow separation of the wing tip is difficult to appear and the winglet drag reduce is effective with limited increased wing span and so on.

关 键 词：商用飞机 翼梢小翼 减阻 翼尖涡 诱导阻力 

分 类 号：V22[航空宇航科学与技术—飞行器设计]