涵道气动优化设计方法

叶坤; 叶正寅; 屈展

涵道气动优化设计方法

西北工业大学航空学院, 西安 710072

基金项目: 航天科技创新基金(201200092)

计量
- 文章访问数: 1660
- HTML浏览量: 30
- PDF量: 1171
- 被引次数: 0
出版历程
- 收稿日期: 2012-09-03
- 刊出日期: 2013-08-28

Aerodynamic optimization method for duct design

School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 基于动量源方法进行涵道气动力的计算,分别采用响应面模型和基于神经网络模型对NASA涵道构型进行优化设计,并对优化结果采用CFD进行验证,优化结果表明两种优化方法均取得了一定的优化效果,悬停状态下,基于响应面方法,涵道拉力增加了19.4%,基于神经网络方法,涵道拉力增加了21.2%.并为了较为细致地研究涵道拉力产生的机理,在对涵道进行建模时,采用一种分区的方法,将涵道划分为6个区域,并得到了涵道拉力在此6个区域上的分布.计算结果表明:涵道唇口形成的负压是产生涵道附加拉力的主要因素,且靠近涵道内侧唇口提供的拉力占比重较大.该优化方法可以有效地应用于涵道外形的气动优化设计中.
- 涵道风扇 /
- 优化设计 /
- 响应面 /
- 神经网络 /
- 遗传算法 /
- 动量源方法 /
- 数值模拟
Abstract: Based on momentum source method of calculating the ducted fan aerodynamic performance,the response surface method and neural network method were applied to aerodynamic optimization design of the NASA duct,and the optimization results were verified by CFD method.The optimization design results show that the two methods have achieved good effect.In the state of hovering,compared with the original duct,duct lift increased by 19.4% based on the response surface method,and duct lift increased by 21.2% based on the neural network method.In addition,in order to study the mechanism of duct lift more carefully,the duct was modeled,and partitioning method was adopted to divide the duct into 6 zones to obtain the duct lift distribution in the 6 regions.This shows that negative pressure formed on duct lip is a main factor to produce additional duct lift,and the duct lip near the interior duct provides higher lift.This optimization method can be effectively applied to the ducted fan aerodynamic optimization design.
- ducted fan /
- optimization design /
- response surface /
- neural network /
- genetic algorithm /
- momentum source method /
- numerical simulation

HTML

参考文献(17)

[1]	Henry L K,Robert A C.Flight operating problems and aerodynamic and performance characteristics of a fixed-wing,tilt-duct,VTOL research aircraft [R].NASA TN D-1802,1963.
[2]	Robert J T,Henry L K.A flight study of the conversion maneuver of a tilt-duct VTOL aircraft [R].NASA TN D-372,1960.
[3]	Yaggy P F,Mort K W.A wind-tunnel investigation of a 4-foot-diameter ducted fan mounted on the tip of a semispan wing [R].NASA TN D-776,1961.
[4]	Parlett L P.Aerodynamic characteristics of a small-scale shrouded propeller at angles of attack from 0° to 90° [R].NACA TN-3547,1955.
[5]	Goodson K W,Grunwald K J.Aerodynamic characteristics of a powered semispan tilting-shrouded-propeller VTOL model in hovering and transition flight [R].NASA TN D-981,1962.
[6]	Mort K W,Gamse B.A wind tunnel investigation of a 7-foot-diameter ducted propeller [R].NASA TN D-4142, 1967.
[7]	Taylor R T.Experimental investigation of the effects of some shroud design variables on the static thrust characteristics of a small-scale shrouded propeller submerged in a wing.NACA TN-4126,1958.
[8]	Grunwald K J,Goodson K W.Aerodynamic loads on an isolated shrouded-propeller configuration for angles of attack from -10° to 10°.NASA TN D-995,1962.
[9]	李建波,高正.涵道风扇空气动力学特性分析[J].南京航空航天大学学报,2005,37(6):680-684. LI Jianbo,GAO Zheng.Aerodynamical characteristics analysis of ducted fan[J].Journal of Nanjing University of Aeronautics & Astronautics,2005,37(6):680-684.(in Chinese)
[10]	徐国华.直升机涵道尾桨与孤立尾桨的气动特性对比研究[J].空气动力学学报,1995,13(4):420-426. XU Guohua.Comparison and analysis of aerodynamic characteristics between helicopter shrouded and isolated tail rotors[J].Acta Aerodynamic Sinica,1995,13(4):420-426.(in Chinese)
[11]	于子文,曹义华.涵道尾桨的CFD模拟与验证[J],航空动力学报,2006,21(1):19-24. YU Ziwen,CAO Yihua.CFD simulation and validation of ducted tail rotor[J].Journal of Aerospace Power,2006,21(1):19-24.(in Chinese)
[12]	熊俊涛,乔志德,韩忠华.响应面方法在跨声速翼型气动优化设计中的应用研究[J].西北工业大学学报,2006,24(2):232-236. XIONG Juntao,QIAO Zhide,HAN Zhonghua.Improving aerodynamic optimization design of transonic airfoils with response surface methodology for design variables as many as about sixteen[J].Journal of Northwestern Polytechnical University,2006,24(2):232-236.(in Chinese)
[13]	邓磊,乔志德,熊俊涛,等.多目标自然层流翼型反设计方法[J].航空学报,2010,31(7):1354-1378. DENG Lei,QIAO Zhide,XIONG Juntao,et al.Multi-objective inverse design of natural laminar flow airfoils[J].Acta Aeronautica et Astronautica Sinica,2010,31(7):1354- 1378.(in Chinese)
[14]	卢险峰.最优化方法应用基础[M].上海:同济大学出版社,2003.
[15]	Hacioglu A.Augmented genetic algorithm with nural network and implementation to the inverse airfoil design [R].AIAA-2004-4633,2004.
[16]	Oyama A,Obayashi S,Nakahashi K,et al.Transonic wing optimization using genetic algorithm [R].AIAA-1997-1854,1997.
[17]	许和勇,叶正寅.涵道螺旋桨与孤立螺旋桨气动特性的数值模拟对比[J].航空动力学报,2011,26(12):2820-2825. XU Heyong,YE Zhengyin.Numerical simulation and comparison of aerodynamic characteristics between ducted and isolated propellers[J].Journal of Aerospace Power,2011,26(12):2820-2825.(in Chinese)