摘要
选择NACA0006系列层流翼型作为物理模型,使用FLUENT商用软件计算分析翼型表面压力梯度,结合对翼型后缘做局部优化修形增大顺压梯度范围以及在翼型前缘布置吸气控制单元并配套吸气装置形成混合层流控制减阻技术。风洞试验中应用红外成像技术测量翼型表面层流区域,探索研究了混合层流控制减阻技术的实用效果。试验结果表明:对翼型实施混合层流控制减阻技术后,明显增大了翼型表面的层流面积。
The main purpose of test study is to find out the effect of drag reduction technique by hybrid laminar flow control. Using NACA0006 series laminar airfoil as physical model, using FLUENT CFD software to calculate and analyse pressure grads of airfoil surface. Uniting optimization local figure of airfoil surface to enlarge positive pressure grads region and disposal leading edge suction control unit of airfoil to come into being drag reduction technique by hybrid laminar flow control. Testing laminar flow area with infrared image in low speed wind tunnel contrasting using drag reduction technique by hybrid laminar flow control and without it. The analysis of the results give the conclusion： the laminar flow area of airfoil surface become larger in evidence after using drag reduction technique by hybrid laminar flow control. The results satisfy the goal of the research.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2010年第1期46-50,共5页
Journal of Experiments in Fluid Mechanics
关键词
层流翼型
混合层流控制
减阻
红外成像技术
laminar flow airfoil
hybrid laminar flow control
drag reduction
infrared imagetechnique
