CORE
🇺🇦
make metadata, not war
Services
Services overview
Explore all CORE services
Access to raw data
API
Dataset
FastSync
Content discovery
Recommender
Discovery
OAI identifiers
OAI Resolver
Managing content
Dashboard
Bespoke contracts
Consultancy services
Support us
Support us
Membership
Sponsorship
Community governance
Advisory Board
Board of supporters
Research network
About
About us
Our mission
Team
Blog
FAQs
Contact us
风洞洞壁对风力机翼型气动特性的影响分析
Authors
张磊
李星星
杨科
白井艳
Publication date
1 January 2016
Publisher
Abstract
本文通过风洞试验测量和计算流体动力学(ComputationalFluidDynamics,CFD)数值模拟的研究结果,分析了风洞洞壁对风力机翼型气动特性的影响.试验风洞为中国科学院工程热物理研究所(InstituteofEngineeringThermophysics,IET)低速回流风洞,所选用的翼型为DU91-W2-250.数值模拟采用有洞壁、无洞壁、无侧壁三种方式进行计算,通过对比试验和数值计算结果验证了采用CFD数值模拟分析风力机翼型洞壁效应的可行性.通过数值模拟分析并与经典映像法及Maskell洞壁修正方法对比,得出:风洞中,上下壁面的存在使流动在风洞壁面形成一定厚度的边界层,造成气流的通道面积减小,来流有效速度增加,并引起翼型升力系数CI和阻力系数Cd增加;风洞侧壁诱导翼型段表面的展向流动、抑制了翼型表面的流动分离,减小了翼型弦向流动速度,引起翼型升力系数减小,阻力系数增加;小攻角时风洞侧壁对翼型表面流动的影响可以忽略,翼段表面流动保持二维性,大攻角时风洞侧壁干扰效应显著,其影响程度超过风洞上下壁面,与无洞壁相比,风洞壁的存在使升力系数减小,阻力系数增加;经典映像法及Maskell方法因未考虑洞壁边界层的影响,并不适用于风力机翼型大攻角流动时的洞壁效应修正问题,大攻角修正时应考虑风洞侧壁影响,对升力系数给予增量;同时对于大攻角流动.翼型本身流动已不具有二维性.其气动性能的测量应采用多截面压力测量或天平测力方法
Similar works
Full text
Available Versions
Institutional Repository of GuangZhou Institute of Energy Conversion, CAS
See this paper in CORE
Go to the repository landing page
Download from data provider
oai:ir.giec.ac.cn:344007/19933
Last time updated on 05/12/2019
Institutional Repository of GuangZhou Institute of Energy Conversion, CAS
See this paper in CORE
Go to the repository landing page
Download from data provider
oai:ir.giec.ac.cn:344007/30069
Last time updated on 04/12/2021
Institutional Repository of GuangZhou Institute of Energy Conversion, CAS
See this paper in CORE
Go to the repository landing page
Download from data provider
oai:ir.giec.ac.cn:344007/19931
Last time updated on 05/12/2019