基于分布式动力的翼身融合飞机整流罩气动设计

doi:10.13700/j.bh.1001-5965.2017.0027

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摘要整流罩设计对基于分布式动力的翼身融合（BWB）飞机气动特性会产生显著影响。为了揭示在边界层吸入（BLI）效应下整流罩的设计参数对飞机气动特性的影响及其原因，采用计算流体力学（CFD）方法和Morris敏感度分析法对此布局飞机气动特性进行了详细研究，得到了整流罩主要设计参数对飞机气动特性影响的敏感度和耦合关系，并对典型设计参数下的流动特性进行分析。结果表明：对飞机气动特性影响较大的参数是整流罩特征截面2和3的最大厚度，这是因为其增大了当地截面的厚度和弯度，进而影响了整流罩表面的压力分布；在流量系数减小和进气边界弦向位置前移时，最大厚度增大会造成背风面发生局部分离；整流罩特征截面2和3的最大厚度对气动特性具有较强的耦合影响。

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	项洋
	吴江浩
	熊峻江

关键词 ：翼身融合(BWB)布局, 边界层吸入(BLI), 计算流体力学(CFD), 敏感度分析, 整流罩

Abstract：Nacelle design has a significant effect on aerodynamic performance of blended-wing-body (BWB) aircraft with distributed propulsion. To clarify the effect and its reason of primary nacelle design parameters on aerodynamic performance of BWB aircraft with boundary layer ingestion (BLI) effect, a detailed study was conducted by computational fluid dynamics (CFD) method and Morris sensitivity analysis method. Sensitivity order and coupled effect of primary design parameters on aerodynamic performance were obtained. Flow details of higher sensitivity and greater coupled effect parameters were analyzed under baseline and alternative condition. The results show that the relatively most significant parameters are the maximum thickness of section 2 and 3. The main reason is that local thickness and camber increase, and pressure distribution of whole nacelle surface is changed. Leeward local stall will occur as the maximum thickness increases configuration when mass flow rate decreases and inlet location along the chord direction moves forward. The coupled effect of the maximum thickness of section 2 and 3 on aerodynamic performance is relatively significant.

Key words： blended-wing-body (BWB) configuration boundary layer ingestion (BLI) computational fluid dynamics (CFD) sensitivity analysis nacelle

收稿日期: 2017-01-16 出版日期: 2017-05-10

PACS:

V221.3

通讯作者: 吴江浩 E-mail: buaawjh@buaa.edu.cn

作者简介: 项洋,男,博士研究生。主要研究方向:飞行器空气动力学;吴江浩,男,博士,教授,博士生导师。主要研究方向:飞行器空气动力学;熊峻江,男,博士,教授,博士生导师。主要研究方向:飞机结构力学。

引用本文:

项洋, 吴江浩, 熊峻江. 基于分布式动力的翼身融合飞机整流罩气动设计[J]. 北京航空航天大学学报, 2018, 44(1): 71-81.
XIANG Yang, WU Jianghao, XIONG Junjiang. Aerodynamic design of nacelle of blended-wing-body aircraft with distributed propulsion. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2018, 44(1): 71-81.

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http://bhxb.buaa.edu.cn/CN/10.13700/j.bh.1001-5965.2017.0027 或 http://bhxb.buaa.edu.cn/CN/Y2018/V44/I1/71

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