Numerical investigation on trailing edge jet and boundary layer ingestion in distributed propulsion system

DUAN Jing-yao; YUAN Wei; LI Qiu-shi

doi:10.13224/j.cnki.jasp.2015.03.007

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Numerical investigation on trailing edge jet and boundary layer ingestion in distributed propulsion system

更新时间：2026-07-07

- Numerical investigation on trailing edge jet and boundary layer ingestion in distributed propulsion system
- Vol. 30, Issue 3, Pages: 571-579(2015)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2015.03.007
  CLC：
- Published：2015
- 稿件说明：
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段静瑶, 袁巍, 李秋实. 分布式动力系统尾缘射流与边界层抽吸的数值分析[J]. 航空动力学报, 2015, 30(3): 571-579.

doi: 10.13224/j.cnki.jasp.2015.03.007
段静瑶, 袁巍, 李秋实. 分布式动力系统尾缘射流与边界层抽吸的数值分析[J]. 航空动力学报, 2015, 30(3): 571-579. DOI： 10.13224/j.cnki.jasp.2015.03.007.

doi: 10.13224/j.cnki.jasp.2015.03.007 DOI：

摘要

为研究带有边界层抽吸的分布式动力系统尾缘射流对机身气动性能及推进效率的影响

将机身简化为二维翼型

并加入尾缘射流及边界层抽吸的作用

利用数值模拟的手段来研究来流攻角、射流偏转角、边界层抽吸对推进效率及气动性能的影响

为分布式动力系统的设计与应用提供初步的建议.结果表明在中、小来流攻角(2°及0.6°)的情况下尾缘射流及边界层抽吸能够提高升阻比

推进效率可超过80%;而在大来流攻角(4°)情况下射流偏转角增大使翼型的阻力大幅上升

对气动性能和推进效率产生极为不利的影响.

Abstract

In order to study the influence of boundary layer ingestion on airframe aerodynamic performance and propulsion efficiency of the distributed propulsion system with trailing edge jet

a two-dimensional airfoil with trailing edge jet and boundary layer ingestion

modeling the airframe

was studied numerically to discuss the influence of incoming angle of attack

jet angle and boundary layer ingestion on aerodynamic performance and propulsion efficiency. Some suggestions on design and application of the distributed propulsion system were carried out. Results show that trailing edge jet and boundary layer ingestion are able to improve the lift-drag ratio at medium/small incoming angle of attack (2° and 0.6°). Propulsion efficiency is able to reach the level over 80%. However

drag of airfoil rises significantly at high incoming angle of attack (4°) with jet angle increasing

resulting in adverse impact on both aerodynamic performance and propulsion efficiency.

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LI Jie

SHI Wenbo

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Related Institution

Department of Precision Instruments, School of Mechanical Engineering, Tsinghua University

The Advanced Aviation Power Innovation Institute

Huiyang Aviation Propeller Company Limited, Aviation Industry Corporation of China, Limited

School of Mechanical and Materials Engineering, North China University of Technology

中国航空发动机集团重大专项工程部

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