摘要
Re=1×10~6的条件下,在S809翼型前缘设置微小圆柱,分别研究了静止及振动的微小圆柱对S809翼型气动性能的影响。数值模拟的结果表明:S809翼型前缘适当位置设置静止及一定振动方式的微小圆柱均能明显降低阻力系数、减小或抑制流动分离区的大小、改善流场状况;在翼型前缘点吸力面正上方6%弦长处,设置直径为2%弦长的静止圆柱可以完全抑制翼型的流动分离;当圆柱直径变小时,静止微小圆柱控制流动分离的效果变差,但此时给圆柱一定规律的振动后,又可以达到较好的流动分离控制效果。
This paper presents a flow control method using mini-cylinder set on the front of the blade leading edge and investigates the aerodynamic performance of S809 airfoil with steady and oscillating cylinder at Re = 1×10~6. Numerical simulation results suggest that this flow control method can effectively reduce the drag coefficient,suppress the flow separation and improve the flow state. Setting a steady cylinder with diameter of 2% chord above the leading edge of 6% chord can completely inhibit the flow separation of the blade. The flow separation inhibition becomes weaker as the diameter of steady cylinder decreases,while that becomes better by using the oscillating cylinder.
出处
《热能动力工程》
CAS
CSCD
北大核心
2017年第8期37-42,共6页
Journal of Engineering for Thermal Energy and Power
基金
国家自然科学基金资助项目(51536006)
上海市科委能力建设项目(17060502300)
关键词
S809
振动圆柱
流动控制
升阻比
S809
oscillating cylinder
flow control
lift-drag ratio
