提高飞机着陆气动性能的一种新方法探索研究

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英文篇名：A new method for improving the aircraft landing performance 作者：叶坤 ; 叶正寅 ; 屈展 英文作者：Ye Kun 1 Ye Zhengyin 1 Qu Zhan 2(National Key Laboratory of Science and Technology on Aerodynamic Design and Research,Northwestern Polytechnical University,710072,Xi’an,China) 1(College of Petroleum Engineering,Xi'an Shiyou University,710065,Xi’an,China) 2 关键词：增升装置 ; 分离涡 ; 大迎角 ; 流动控制 ; 数值模拟 英文关键词：lift device,separated vortex,high angle of attack,the controlling of stream,numerical simulation. 中文刊名：YYLX 英文刊名：Chinese Journal of Applied Mechanics 机构：西北工业大学翼型叶栅空气动力学国家级科技重点实验室;西安石油大学石油工程学院; 出版日期：2012-12-15 出版单位：应用力学学报 年：2012 期：v.29;No.118 基金：国家自然科学基金(11072199) 语种：中文; 页：YYLX201206002 页数：8 CN：06 ISSN：61-1112/O3 分类号：18-24+152

摘要

提出了一种新型气动技术,其主要原理是:将机翼上表面的一部分翼面设计为活动翼面,当飞机进入降落阶段、迎角较大时,适当抬高该活动翼面,从而在该活动翼面后形成一个台阶,通过台阶中产生的稳定驻涡来控制机翼上表面的流动;与此同时,打开安装在机翼上的Gurney襟翼,可达到同时提高机翼升力和失速迎角的目的。将该技术在DLR-F4上应用,数值模拟结果表明:机翼的最大升力系数提高了17.37%;失速迎角从11°提高到13°,提高了18.18%。本文为提高飞机的着落性能探索出一种具有发展潜力的方法。
        A new aerodynamic technique is presented.The main principle is to design a movable part on the upper surface of the wing.When the aircraft access to the relatively larger angle of attack in the period of landing,a step can be formed by appropriately raising the downstream tip of the movable part,thus a stable trapped vortex is generated to control the flow above the upper surface of the wing.At the same time,the Gurney flap which is installed at the trailing-edge of the wing is operated.Both effects of enlarging the lift and the stall angle of attack will be achieved.By the numerical simulation of DLR-F4,it is shown that the airfoil’s maximum lift coefficient can be increased by 17.37%,and the stall angle of attack increases from 11 degree to 13 degree(increased by 18.18%).It is believed that the method presented to be a promising one for improving the aircraft landing performance for the small aircraft.

引文

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