大型运输机动力增升喷流效应数值模拟

龚志斌; 李杰; 蒋胜矩; 张恒

doi:10.13224/j.cnki.jasp.2016.08.003

大型运输机动力增升喷流效应数值模拟

doi: 10.13224/j.cnki.jasp.2016.08.003

1. 西北工业大学航空学院, 西安 710072;
2. 中国兵器工业集团公司西安现代控制技术研究所, 西安 710065

基金项目:

国家自然科学基金（11172240）；航空科学基金（2014ZA53002）；国家重点基础研究发展计划（2015CB755800）

详细信息

作者简介:
龚志斌(1986-),男,江西吉安人,博士生,主要从事理论与计算空气动力学研究.

中图分类号: V211.3
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- 文章访问数: 1010
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出版历程
- 收稿日期: 2014-11-14
- 刊出日期: 2016-08-28

Numerical simulation of powered high-lift jet effects for large transport

1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072;
2. Xi'an Modern Control Technology Research Institute, China North Industries Group Corporation, Xi'an 710065, China

摘要

摘要: 参照C-17运输机发动机安装位置，考虑内、外涵道分开排气，建立了外吹式襟翼动力增升全机几何分析模型以及相应的巡航构型.采用结构化多块网格技术，基于雷诺平均Navier-Stokes方法，分别对全机增升构型和单独发动机动力喷流进行数值模拟验证，在此基础上对外吹式襟翼动力喷流效应展开研究.对于低速动力增升构型，发动机喷流大部分直接冲刷襟翼下表面而后向下偏转，部分高速气流经襟翼缝道引射并加速后吹向襟翼上表面，两部分气流在襟翼后缘汇合并向下游延伸，喷流冲刷襟翼时存在明显展向横流特征.在动力喷流影响下，不仅襟翼环量大幅增加，缝翼和主翼上的环量也均有所增加，全机可用升力系数和最大升力系数均突破了机械式增升装置的极限，达到4.0以上.同时，全机低头力矩大幅增加，为纵向配平带来额外的压力.对于相应的高速巡航构型，发动机喷流主要影响机翼下表面的压力分布，使得全机升力减小，阻力明显增大.动力增升构型在基本翼设计过程中应充分考虑喷流的影响.
- 外吹式襟翼 /
- 动力增升 /
- 结构化多块网格 /
- 雷诺平均Navier-Stokes方法 /
- 动力喷流效应
Abstract: Taking C-17 transport engine installation as reference and considering external mixing of engine jet gas streams, a powered high-lift configuration with externally blowing flap (EBF) and the corresponding cruise model were constructed. Based on the structured multi-block grid techniques and Reynolds-averaged Navier-Stokes methods, numerical validations were carried out on a high-lift model and a fan-jet engine nacelle, and then the EBF effects were investigated. For powered high-lift configuration at low speed, most jet flow impinged directly on the lower flap surfaces and then deflected downward, while the rest was sucked and speeded up by the slots, and then blown upon the upper flap surfaces. The two parts of them converged at the flap trailing edge and extended downward. Spanwise lateral flow characteristics existed when the jet flow affected on the flap. Circulations increased significantly not just around the flaps but also on the slat and main wing. Both the available and maximum lift coefficients were larger than 4.0, breaking through the limit of the traditional mechanical high-lift systems. Longitude trim problems may be severer due to larger nose down pitching moment. For the cruise model at high speed, the engine jet flow will obviously affect the pressure distributions on lower wing surface, making the lift decrease and the drag increase significantly. Thus jet effects should be well considered during the clean wing design for powered high-lift configuration.
- externally blowing flap /
- powered high-lift /
- structured multi-block grid /
- Reynolds-averaged Navier-Stokes methods /
- power jet effects

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参考文献(18)

[1]	Kimberlin R D,Sinha A K.STOL attack aircraft design based upon an upper surface blowing concept[R].AIAA 83-2535,1983.
[2]	White A,Yaros S F,Sexstone,M G,et al.Synergistic airframe-propulsion interactions and integrations[R].NASA TM-1998-207644,1998.
[3]	Deckert W H,Frankin J A.Powered-lift aircraft technology[R].NASA SP-501,1989.
[4]	戴思宗,董建鸿.外吹式动力增升技术在大型运输机上的应用研究[J].航空科学技术,2006,17(2):33-38. DAI Sizong,DONG Jianhong.A study of externally blowing powered-lift technique for application to large transport[J].Aeronautical Science and Technology,2006,17(2):33-38.(in Chinese)
[5]	Slotnick J P,An M Y,Mysko S J,et al.Navier-Stokes analysis of a high wing transport high-lift configuration with externally blown flaps[R].AIAA-2000-4219,2000.
[6]	Griffin H A,Gonzalez L F,Shrinivas K.Computational fluid dynamics analysis of externally blown flap configuration for transport aircraft[J].Journal of Aircraft,2008,45(1):172-184.
[7]	李少飞,李杰,刘正宾.外吹式襟翼动力增升绕流数值分析[J].航空计算技术,2008,38(5):45-47. LI Shaofei,LI Jie,LIU Zhengbin.Numerical simulation of externally blown flap with powered-lift flow[J].Aeronautical Computing Technique,2008,38(5):45-47.(in Chinese)
[8]	刘李涛,杨永,李喜乐.外吹式动力吹气襟翼NS方程数值分析[J].航空计算技术,2008,38(3):61-64. LIU Litao,YANG Yong,LI Xile.Numerical analysis of high-lift system with externally blown flap using N-S equations[J].Aeronautical Computing Technique,2008,38(3):61-64.(in Chinese)
[9]	郭少杰,王豪杰,李杰.外吹式襟翼动力增升数值模拟方法研究[J].航空工程进展,2010,1(1):49-54. GUO Shaojie,WANG Haojie,LI Jie.Numerical simulating method for powered high-lift flow[J].Advances in Aeronautical Science and Engineering,2010,1(1):49-54.(in Chinese)
[10]	郭少杰.下吹式襟翼动力增升效能数值模拟分析研究[D].西安:西北工业大学,2010. GUO Shaojie.The aerodynamic performance analysis and design for high-lift configuration aircraft[D].Xi'an:Northwestern Polytechnical University,2010.(in Chinese)
[11]	李鑫,李杰,刘城斌.外吹式襟翼动力增升的机理研究[J].应用力学学报,2013,30(2):141-147. LI Xin,LI Jie,LIU Chengbin.Flow theory investigation of externally blown flap powered high-lift configuration[J].Chinese Journal of Applied Mechanics,2013,30(2):141-147.(in Chinese)
[12]	李鑫.外吹式襟翼动力增升数值模拟研究[D].西安:西北工业大学,2013. LI Xin.The aerodynamic performance analysis and design for high-lift configuration aircraft[D].Xi'an:Northwestern Polytechnical University,2013.(in Chinese)
[13]	LI Jie,E Qin,LI Fengwei,et al.3-D flow simulations for general powered engine nacelles using Euler equations[R].AIAA 98-0929,1998.
[14]	谭兆光,陈迎春,李杰等.机体/动力装置一体化分析中的动力影响效应数值模拟[J].航空动力学报,2009,24(8):1766-1772. TAN Zhaoguang,CHEN Yingchun,LI Jie,et al.Numerical simulation method for the powered effects in airframe/propulsion integration analysis[J].Journal of Aerospace Power,2009,24(8):1766-1772.(in Chinese)
[15]	Slotnick J P,Hannon J A,Chaffin M.Overview of the first AIAA CFD high lift prediction workshop[R].AIAA-2011-862,2011.
[16]	Park M A,Lee-Rausch E M,Rumsey C L.FUN3D and CFL3D computations for the first high lift prediction workshop[R].AIAA-2011-936,2011.
[17]	Hirose N,Asai K,Ikawa K.Transonic 3-D Euler analysis of flows around fan jet engine and turbine powered simulator[R].NAL-TR-1045,1989.
[18]	Hirose N,Asai K,Ikawa K,et al.3-D Euler flow analysis of fan jet engine and turbine powered simulator with experimental comparison in transonic speed[R].AIAA 89-1835,1989.