民用飞机低速俯仰力矩特性改善研究

钟园; 杨小权; 刘凯礼; 吴大卫; 司江涛

doi:10.7638/kqdlxxb-2017.0097

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民用飞机低速俯仰力矩特性改善研究

研究论文 | 更新时间：2026-05-28

- 民用飞机低速俯仰力矩特性改善研究
- Study on improvement of low speed pitching moment characteristics of civil aircraft
- 空气动力学学报 2019年37卷第4期页码：569-577
- 作者机构：
  
  中国商用飞机有限责任公司上海飞机设计研究院,上海,201210
- 作者简介：
  
  钟园(1986-), 男, 湖北枝江人, 硕士, 高级工程师, 研究方向:飞机气动布局, 气动设计.E-mail:zhongyuan@comac.cc
  司江涛(1969-), 男, 陕西咸阳人, 硕士, 研究员, 研究方向:飞机气动布局, 气动设计.E-mail:sijiangtao@comac.cc
- 基金信息：
  
  国家重点基础研究发展计划(1234AB5678);上海市青年科技英才杨帆计划(15YF1415000)
- DOI：10.7638/kqdlxxb-2017.0097
  中图分类号： V221+.3
- 纸质出版：2019
- 稿件说明：
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钟园, 杨小权, 刘凯礼, 吴大卫, 司江涛. 民用飞机低速俯仰力矩特性改善研究[J]. 空气动力学学报, 2019, 37(4): 569-577.

ZHONG Yuan, YANG Xiaoquan, LIU Kaili, et al. Study on improvement of low speed pitching moment characteristics of civil aircraft[J]. 2019, 37(4): 569-577.
钟园, 杨小权, 刘凯礼, 吴大卫, 司江涛. 民用飞机低速俯仰力矩特性改善研究[J]. 空气动力学学报, 2019, 37(4): 569-577. DOI： 10.7638/kqdlxxb-2017.0097.

ZHONG Yuan, YANG Xiaoquan, LIU Kaili, et al. Study on improvement of low speed pitching moment characteristics of civil aircraft[J]. 2019, 37(4): 569-577. DOI： 10.7638/kqdlxxb-2017.0097.

摘要

针对某民用尾吊飞机低速时俯仰力矩上仰的情况，研究了一种新型的改善措施——内侧缝翼截短。采用数值模拟方法对其基本着陆构型以及改善措施的气动特性进行研究，给出了在大迎角下工作的流场特征，分析了改善措施改善俯仰力矩特性的流动机理，并对改善措施对发动机进气畸变的影响进行了评估。研究结果表明：低速俯仰力矩形态取决于机翼的分离位置；分离从外侧开始会使飞机"抬头"，分离从内侧开始会使飞机"低头"；平尾提供的俯仰力矩决定了总的俯仰力矩；分离从内侧开始使飞机"低头"的主要原因是降低了机翼对平尾的下洗；改善措施在失速迎角内不会对尾吊飞机的发动机进气产生影响。

Abstract

For the situation that the pitching moment of a civil fuselage-mounted aircraft shows to pitch up

the paper studied a new type of improvement measures-to truncate the inner slat. The numerical simulation method was used to study the aerodynamic characteristics of the basic landing configuration and the improvement configuration. The flow characteristics of the two configurations under the high angle of attack are given

and the flow mechanism of the improvement measures is analyzed. The influence of the improvement measures on the intake of the engine is also evaluated. The results show that:the low-speed pitching moment shape depends on the separation position of the wing; separation from the inside wing makes the aircraft "rise"; separation from the outer wing makes the aircraft "head"

and separation from the inside wing makes the aircraft "bow"; the pitching moment provided by the horizontal tail determines the total pitching moment; the main reason for the aircraft "bow" is that the separation from the inside wing reduces the downwash of the horizontal tail from the wing; the improvement measures do not affect the engine intake of the fuselage-mounted aircraft when the angle of attack is not greater than the stall angle of attack.

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