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论文:2015,Vol:33,Issue(3):353-360 |
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引用本文： |
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张乐, 周洲, 许晓平, 王红波. 飞翼无人机保形进排气系统动力数值模拟与流场特性分析[J]. 西北工业大学学报 |
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Zhang Le, Zhou Zhou, Xu Xiaoping, Wang Hongbo. Numerical Simulation of Power and Flow Field Characteristics of Conformal Intake and Exhaust for Flying Wing Unmanned Aerial Vehicle[J]. Northwestern polytechnical university |
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| 飞翼无人机保形进排气系统动力数值模拟与流场特性分析 |
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| 张乐, 周洲, 许晓平, 王红波 |
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| 西北工业大学 无人机特种技术国防科技重点实验室, 陕西 西安 710065 |
| 摘要: |
| 利用计算流体力学(CFD)方法,分别针对保形进气道和膨胀尾喷管风洞试验模型进行数值模拟,验证了模拟进排气动力边界条件的可靠性。再基于飞翼布局无人机双发动机布局下隐身与保形设计要求,设计了矩形进气口S弯进气道和圆矩形喷口尾喷管,并利用数值模拟方法对无人机进排气系统进行了计算分析,获得了无人机全机气动性能及进排气三维流场特性。研究表明:①进排气使得飞翼无人机升阻特性有所下降,但低马赫数(0.5,0.6)下能改善无人机俯仰力矩特性;②随着马赫数增加,进气道总压恢复系数减小且畸变指数增加,而尾喷管轴向推力系数则升高,且推力性能保持较好;高马赫数(0.7)下进气道特性下降较快,设计时应多考虑飞行包线右边界;③侧滑角对于进气道性能影响较大,而尾喷管推力性能受侧滑角影响较小,设计时应多考虑进气道侧滑影响。 |
| 关键词:
飞翼无人机
保形进气道
膨胀尾喷管
进排气
总压恢复系数
畸变指数
轴向推力系数
流场特性
数值模拟
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| Numerical Simulation of Power and Flow Field Characteristics of Conformal Intake and Exhaust for Flying Wing Unmanned Aerial Vehicle |
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| Zhang Le, Zhou Zhou, Xu Xiaoping, Wang Hongbo |
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| National Key Laboratory of Science and Technology on UAV, Northwestern Polytechnical University, Xi'an 710072, China |
| Abstract: |
| Using computational fluid dynamics (CFD) method, we performed numerical simulations on the wind tunnel test model of conformal inlet and expansion nozzle; they were aimed at verifying the reliability of the boundary conditions on power simulation. Keeping in mind the stealth and conformal requirements of twin-engine flying wing UAV, we designed a S-shaped inlet with rectangular intake and a circular-rectangle nozzle. And then numerical simulation was carried out on the intake and exhaust system, and it was also applied to studying the aerodynamic performance of UAV and three-dimensional flow field characteristics of the intake and exhaust. Results and their analysis indicate:(1)the lift/drag characteristic of flying wing UAV declines when adopting the intake and exhaust, but it can be used to improve the longitudinal moment characteristic under the low Mach number 0.5 and 0.6;(2)with increasing Mach number, the total pressure recovery coefficient decreases and the distortion coefficient increases, while the axial thrust coefficient increases and the thrust performance remains relatively satisfactory; the inlet performance decreases rapidly at the high Mach number 0.7;so we should pay more attention to the right border of the flight envelope in the design;(3)the sideslip angle exerts greater influence on the inlet performance, while the thrust performance of nozzle is less affected;so we also should pay more attention to the impact of sideslip angle on inlet. |
| Key words:
angle of attack
boundary conditions
computational fluid dynamics
computer simulation
design
exhaust systems
experiments
flight envelopes
flow fields
flow rate
inlet flow
intake systems
lift drag ratio
Mach number
mathematical models
mesh generation
Navier Stokes equations
nozzles
pressure distribution
reliability
schematic diagrams
stealth technology
three dimensional
turbulence models
unmanned aerial vehicles(UAV)
axial thrust coefficient
conformal inlet
distortion coefficient
expansion nozzle
flow field characteristics
flying wing UAV
total pressure recovery coefficient
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| 收稿日期: 2014-10-28
修回日期:
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| DOI: |
| 基金项目: 国家自然科学基金(11302178)与航空科学基金(2013ZA53002)资助 |
| 通讯作者:
Email： |
| 作者简介: 张乐(1988—),西北工业大学博士研究生,主要从事飞行器总体设计、气动隐身一体化研究。
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| 作者相关文章 |
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| 张乐 在本刊中的所有文章 |
| 周洲 在本刊中的所有文章 |
| 许晓平 在本刊中的所有文章 |
| 王红波 在本刊中的所有文章 |
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相关文献: |
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1．张乐, 周洲, 李盈盈, 甘文彪, 许晓平.飞翼无人机保形非对称尾喷管设计与流场特性[J]. 西北工业大学学报, |
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