翼身融合民机扰流板增升技术

doi:10.7527/S1000-6893.2019.23045

翼身融合民机技术专栏

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翼身融合民机扰流板增升技术

王刚¹, 张明辉¹, 毛俊², 桑为民¹, 陈真利¹, 王龙³, 张彬乾¹

1. 西北工业大学航空学院, 西安 710072;
2. 中国商用飞机有限责任公司上海飞机设计研究院, 上海 201210;
3. 航空工业惠阳航空螺旋桨有限责任公司, 保定 071051

收稿日期:2019-03-25 修回日期:2019-04-03 出版日期:2019-09-15 发布日期:2019-05-10
通讯作者: 陈真利 E-mail:zhenlichen@nwpu.edu.cn
基金资助:
中央高校基本科研业务费专项资金（3102019JC009，G2016KY0002）

High-lift technology for spoiler on blended-wing-body civil aircraft

WANG Gang¹, ZHANG Minghui¹, MAO Jun², SANG Weimin¹, CHEN Zhenli¹, WANG Long³, ZHANG Binqian¹

1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. Shanghai Aircraft Design and Research Institute, Commercial Aircraft Corporation of China, Ltd., Shanghai 201210, China;
3. AVIC Huiyang Aviation Propeller Co., Ltd., Baoding 071051, China

Received:2019-03-25 Revised:2019-04-03 Online:2019-09-15 Published:2019-05-10
Supported by:
The Fundamental Research Funds for the Central Universities (3102019JC009, G2016KY0002)

摘要/Abstract

摘要： 为满足翼身融合（BWB）民机增升装置简单、高效的设计需求，以配置三段高升力系统的BWB民机增升构型为对象，采用数值模拟方法研究了下偏扰流板技术的增升机理与设计原则。研究结果表明，设计合理的下偏扰流板能够将BWB民机增升构型设计点升力系数提高约20%；其增升机理集中体现为对缝道射流、流场能量分布、环量及其分布的控制作用。其应用于BWB民机增升装置的设计原则为：扰流板偏转后上表面延长线应与襟翼上表面相切，控制缝道宽度使增升装置环量增大并前移，控制扰流板偏度避免扰流板内段过早分离。研究还表明，受增升装置三维效应影响，扰流板下偏翼型上洗作用越强，则相应三维增升装置升力损失越大，并呈近似线性变化规律。下偏扰流板改造简单，且有助于简化襟翼作动机构，是一种很有潜力的增升技术，具有深入研究的价值和良好的应用前景。

关键词: 翼身融合, 民机, 增升装置, 下偏扰流板, CFD

Abstract: To meet the design requirements for the high-lift device of Blended-Wing-Body (BWB) civil aircraft with simplicity and high efficiency, the BWB high-lift configuration with three-element high-lift device is numerically simulated to study the mechanism of lift-enhancement and design principles of the drooped spoiler technology. The research results show that the reasonable design of the drooped spoiler can increase the design point lift coefficient of the BWB high-lift configuration by almost 20%. The lift-enhancement mechanism of the drooped spoiler is mainly concentrated on the control of the slot-jet, the energy distribution of the flow field, the circulation, and its distribution. The design principles of the drooped spoiler for BWB civil aircraft are as follows:the deflection of the drooped spoiler should be tangent to the upper surface of the flap; the gap width should be narrowed to enhance the circulation and move it forward; and the deflection of the internal spoiler should be limited to avoid premature separation. The study also shows that, with the influence of the three-dimensional effect of the high-lift device, the stronger the up-washing effect of spoiler deflected airfoils, the greater the lift loss of the three-dimensional high-lift device, showing an almost linear pattern of variation. Since it is simple to reconstruct and helps to simplify the flap operating mechanism, the drooped spoiler is a potential high-lift improvement technology, demonstrating in-depth research values and good application prospects.

Key words: blended-wing-body, civil aircraft, high-lift device, drooped spoiler, CFD

中图分类号:

V211.4

王刚, 张明辉, 毛俊, 桑为民, 陈真利, 王龙, 张彬乾. 翼身融合民机扰流板增升技术[J]. 航空学报, 2019, 40(9): 623045-623045.

WANG Gang, ZHANG Minghui, MAO Jun, SANG Weimin, CHEN Zhenli, WANG Long, ZHANG Binqian. High-lift technology for spoiler on blended-wing-body civil aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(9): 623045-623045.

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翼身融合民机扰流板增升技术

High-lift technology for spoiler on blended-wing-body civil aircraft

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