飞翼布局无人机喷流对气动特性影响研究

张翔; 曹德一; 何海波; 崔飞

doi:10.7638/kqdlxxb-2017.0052

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飞翼布局无人机喷流对气动特性影响研究

研究论文 | 更新时间：2026-05-28

- 飞翼布局无人机喷流对气动特性影响研究
- Influence investigation of engine exhaust on aerodynamic performance for the flying wing UAV
- 空气动力学学报 2019年37卷第4期页码：578-585
- 作者机构：
  
  北京机电工程研究所,北京,100074
- 作者简介：
  
  张翔(1989-), 男, 陕西人, 工程师, 硕士研究生, 研究方向:飞行器气动设计.E-mail:zx906@126.com
  何海波(1976-), 男, 黑龙江人, 研究员, 硕士研究生, 研究方向:飞行器气动设计.E-mail:hehaibo@163.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2017.0052
  中图分类号： V221.3
- 纸质出版：2019
- 稿件说明：
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张翔, 曹德一, 何海波, 崔飞. 飞翼布局无人机喷流对气动特性影响研究[J]. 空气动力学学报, 2019, 37(4): 578-585.

ZHANG Xiang, CAO Deyi, HE Haibo, et al. Influence investigation of engine exhaust on aerodynamic performance for the flying wing UAV[J]. 2019, 37(4): 578-585.
张翔, 曹德一, 何海波, 崔飞. 飞翼布局无人机喷流对气动特性影响研究[J]. 空气动力学学报, 2019, 37(4): 578-585. DOI： 10.7638/kqdlxxb-2017.0052.

ZHANG Xiang, CAO Deyi, HE Haibo, et al. Influence investigation of engine exhaust on aerodynamic performance for the flying wing UAV[J]. 2019, 37(4): 578-585. DOI： 10.7638/kqdlxxb-2017.0052.

摘要

采用计算流体力学方法，针对飞翼布局无人机涡扇发动机喷流问题开展了数值模拟研究。首先，应用Reynolds平均Navier-Stokes方程数值模拟方法，对典型飞翼布局无人机数值模拟进行了网格无关性验证；其次，探讨了在工程设计中，由于喷流导致无人机产生的外形变化带来的气动特性差异；最后，针对典型工况下不同落压比喷流条件，研究分析了涡扇发动机喷流效应对无人机气动特性的影响规律。研究结果表明：喷流导致飞翼布局无人机外形发生变化，因此带来6%~9%阻力系数的增量，并使俯仰力矩系数下移；而喷流效应主要影响无人机阻力系数和俯仰力矩系数，影响规律随落压比而变化。

Abstract

The turbofan engine exhaust simulation is carries out for the flying wing UAV by the means of computational fluid dynamics. Firstly

the grid convergence study is performed with course

medium

and fine grid systems for the flying wing UAV through Reynolds-averaged Navier-Stokes equations and structured grid technology. Secondly

the change of the aerodynamic performance caused by the difference between the flying wing configuration with engine exhaust and without engine exhaust is discussed in the engineering design. Lastly

the turbofan engine exhaust effect is studied with three different nozzle pressure ratio conditions. The study shows that

the change of the configuration generated by engine exhaust makes the drag increased 6%-9% and pitching moment decreases. The engine exhaust has an effect on drag coefficient and pitching moment coefficient

and the influence quantities are varied with the nozzle pressure ratio.

关键词

Keywords

references

YU Y G, HUANG Y, ZHOU Z, et al. Aerodynamic design of a flying-wing aircraft[J]. Acta Aerodynamic Sinica, 2017, 35(6):832-836.

MIALAN B, FOL T. Aerodynamic optimization of subsonic flying wing configurations. AIAA 2002-2931[R]. Reston: AIAA, 2002.

ZHANG L, ZHOU Z, XU X P, et al. Numerical simulation of power and flow field characteristics of conformal intake and exhaustfor flying wing unmanned aerial vehicle[J]. Journal of Northwestern Polytechnical University, 2015, 33(3):353-360. (in Chinese)

TAN Z G, CHEN Y C. Numerical simulation method for the powered effects in airframe/propulsion integration analysis[J]. Journal of Aerospace Power, 2009, 8(8):1766-1772. (in Chinese)

YU X H, TAO Y J, SHI X J. Effect of engine air intake and exhaust on the aerodynamic performance of the UAV[J]. Flight Dynamics, 2011, 29(5):18-21. (in Chinese)

LI J T. Research of th flying wing flight quality in high altitude and long endurance unmanned aerial vehicle[D]. Xi'an: Northwest Polytechnical University, 2007. (in Chinese)

HUANG S Q, SHEN G X, ROBERT KONRATH, et al. Experimental investigation of influence of jets on aircraft wake vortices[J]. Acta Aeronautica et Astronutica Sinica, 2010, 31(5):899-908. (in Chinese)

LI Z F. Wind tunnel experiment technology[M]. Beijing:Aviation Industry Press, 2010:153-184. (in Chinese)

MAHMOOD G M, SMITH D R.Proportional aerodynamic control of a UAV wing model using synthetic jets[R]. AIAA 2007-3851, 2007.

DAVID C WILCOX. Turbulence modeling for CFD[M]. Third edition. California: DCW Industries Inc, 2006: 243-249.

YAN C. Computational methods and application[M]. 2nd ed. Beijing:Beihang university press, 2006:221-223. (in Chinese)

MENTER F R. Two-equation eddy-viscosity turbulence models for engineering application[J]. AIAA Journal, 1994, 32(8):1598-1605.

ZHANG X, YAN C. Property evaluation on turbulence models calculation in hypersonic heat transfer simulation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(2):337-342.

ROE P L. Approximate Riemann solvers' parameter vectors and difference schemes[J]. Comp Phys, 1982, 170:507-512.

VAN LEER B. Towards the ultimate conservation different schemeV:a second-order sequal to Godunov's methods[J]. Journal of Computational Physics, 2004, 201(1):238-260.

WANG Y T, SUN Y, WANG G X, et al. High-order accuracy numerical simulation of DLR-F6 wing-body configuration[J]. Acta Aeronautica et Astronutica Sinica, 2015, 36(9):2923-2929. (in Chinese)

FAN J C. Handbook of wind tunnel test[M]. Beijing:Aviation Industry Press, 2002:369-374. (in Chinese)

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