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

北京航空航天大学学报 ›› 2018, Vol. 44 ›› Issue (1): 71-81.doi: 10.13700/j.bh.1001-5965.2017.0027

基于分布式动力的翼身融合飞机整流罩气动设计

项洋, 吴江浩, 熊峻江

北京航空航天大学交通科学与工程学院, 北京 100083

收稿日期:2017-01-16 修回日期:2017-02-06 出版日期:2018-01-20 发布日期:2017-05-10
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。

Aerodynamic design of nacelle of blended-wing-body aircraft with distributed propulsion

XIANG Yang, WU Jianghao, XIONG Junjiang

School of Transportation Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

Received:2017-01-16 Revised:2017-02-06 Online:2018-01-20 Published:2017-05-10

摘要/Abstract

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。

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

中图分类号:

V221.3

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[J]. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2018, 44(1): 71-81.

参考文献

[1] LIEBECK R H.Design of the blended wing body subsonic transport[J].Journal of Aircraft,2004,41(1):10-25.
[2] QIN N,VAVALLE A,MOIGNE L A,et al.Aerodynamic considerations of blended wing body aircraft[J].Progress in Aerospace Sciences,2004,40(6):321-343.
[3] LABAN M,ARENDSEN P,ROUWHORST W,et al.A computational design engine for multi-disciplinary optimisation with application to a blended wing body configuration[C]//9th AIAA/ASSMO Multidisciplinary Analysis and Optimization Conference.Reston:AIAA,2002.
[4] KIM H,LIOU M F,LIOU M S.Mail-slot nacelle shape design for N3-X hybrid wing body configuration[C]//51st AIAA/SAE/ASEE Joint Propulsion Conference.Reston:AIAA,2015:3805.
[5] KO A.The multidisciplinary design optimization of a distributed propulsion blended-wing-body aircraft[D].Blacksburg:Virgina Polytechnic Institute and State University,2003.
[6] GOHARDANI A S,DOULGERIS G,SINGH R.Challenges of future aircraft propulsion:A review of distributed propulsion technology and its potential application for the all electric commercial aircraft[J].Progress in Aerospace Sciences,2011,47(5):369-391.
[7] KIM H D,BROWN G V,FELDER J L.Distributed turboelectric propulsion for hybrid wing body aircraft[C]//9th International Powered Lift Conference.London:Royal Aeronautical Society,2008.
[8] HILEMAN J I,SPAKOVSZKY Z S,DRELA M,et al.Airframe design for silent fuel-efficient aircraft[J].Journal of Aircraft,2010,47(3):956-969.
[9] KO A,LEIFSSON L T,SCHETZ J A,et al.MDO of a blended-wing-body transport aircraft with distributed propulsion:AIAA-2003-6732[R].Reston:AIAA,2003.
[10] KO A,SCHETZ J A,MASON W H.Assessment of the potential advantages of distributed-propulsion for aircraft[C]//XVIth International Symposium on Air Breathing Engines (ISABE).Reston:AIAA,2003:71-79.
[11] RODRIGUEZ D L.Multidisciplinary optimization method for designing boundary-layer-ingesting inlets[J].Journal of Aircraft,2009,46(3):883-894.
[12] LUNDBLADH A,GRÖNSTEDT T.Distributed propulsion and turbofan scale effects[C]//ISABE 2005,17th Symposium on Airbreathing Engine.Reston:AIAA,2005.
[13] LIOU M S,KIM H J,LIOU M F.Aerodynamic design of the hybrid wing body with nacelle:N3-X propulsion-airframe configuration[C]//34th AIAA Applied Aerodynamics Conference.Reston:AIAA,2016:3875.
[14] 闫万方,吴江浩,张艳来.分布式推进关键参数对BWB飞机气动特性影响[J].北京航空航天大学学报,2015,41(6):1055-1065.YAN W F,WU J H,ZHANG Y L.Effects of distributed propulsion crucial variables on aerodynamic performance of blended wing body aircraft[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(6):1055-1065(in Chinese).
[15] 项洋,吴江浩,张艳来.BLI效应下整流罩设计对翼型气动特性的影响[J].北京航空航天大学学报,2016,42(5):945-952.XIANG Y,WU J H,ZHANG Y L.Effects of cowling design on aerodynamic performance of airfoil with BLI[J].Journal of Beijing University of Aeronautics and Astronautics,2016,42(5):945-952(in Chinese).
[16] NICHOLS M R,KEITH A L.Investigation of a systematic group of NACA 1-series cowlings with and without spinners:NACA-Report-950[R].Washington,D.C.:U.S.Government Printing Office,1950.
[17] MORRIS M D.Factorial sampling plans for preliminary computational experiments[J].Technometrics,1991,33(2):161-174.

基于分布式动力的翼身融合飞机整流罩气动设计

Aerodynamic design of nacelle of blended-wing-body aircraft with distributed propulsion

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	丁红兵, 李一鸣, 李金霞, 王超. 微型探头-传感系统高频响应特性模型适应性[J]. 北京航空航天大学学报, 2019, 45(8): 1519-1528.
[2]	高国富, 李康, 李瑜, 向道辉, 赵波. 超声激励薄液膜Faraday波形成机理[J]. 北京航空航天大学学报, 2019, 45(8): 1582-1588.
[3]	王晨臣, 冯诗愚, 彭孝天, 邓阳, 陈俊. 发动机短舱泄压过程瞬态仿真[J]. 北京航空航天大学学报, 2019, 45(11): 2284-2290.
[4]	邸浩宇, 徐晶磊, 高歌. 龙卷风维持特性的探索[J]. 北京航空航天大学学报, 2018, 44(5): 1110-1116.
[5]	孟繁超, 董素君, 江泓升, 王浚. 长时间流固耦合传热过程的快速算法[J]. 北京航空航天大学学报, 2017, 43(6): 1224-1230.
[6]	鞠胜军, 阎超, 叶志飞. 吸气式高超声速飞行器多参数灵敏度分析[J]. 北京航空航天大学学报, 2017, 43(5): 927-934.
[7]	杜思亮, 吉孟江, 唐正飞, 陈仁良. 基于横流风扇技术的直升机反扭验证[J]. 北京航空航天大学学报, 2017, 43(5): 981-991.
[8]	赵雅甜, 阎超, 孙迪, 屈峰. 新型三阶TVD限制器性能分析[J]. 北京航空航天大学学报, 2017, 43(4): 800-805.
[9]	胡健, 王楠, 胡洋. 加速导管和减速导管的性能比较[J]. 北京航空航天大学学报, 2017, 43(2): 240-252.
[10]	林博希, 阎超, 李亚超. 喷流干扰气动热数值模拟的若干影响因素[J]. 北京航空航天大学学报, 2016, 42(6): 1210-1218.
[11]	李嘉, 李华聪, 王淑红, 徐轩. 多级导流诱导轮与叶轮一体型线优化[J]. 北京航空航天大学学报, 2016, 42(5): 953-960.
[12]	项洋, 吴江浩, 张艳来. BLI效应下整流罩设计对翼型气动特性的影响[J]. 北京航空航天大学学报, 2016, 42(5): 945-952.
[13]	申晓斌, 林贵平, 杨胜华. 三维发动机进气道水滴撞击特性分析[J]. 北京航空航天大学学报, 2011, 37(1): 1-5.
[14]	张小伟, 王延荣, 谢胜百, 单鹏. 弹性整流罩分离的流固耦合仿真方法[J]. 北京航空航天大学学报, 2009, 35(8): 976-979.
[15]	艾宁, 樊建华,李育敏. 全玻璃真空管型太阳热水器内流场的CFD模拟[J]. 北京航空航天大学学报, 2008, 34(10): 1195-1199.