A direct numerical simulation (DNS) around a 2-D airfoil was carried out through high order finite difference scheme, the Reynolds number based on chord is 1.0×104, the angle of attack is 3°. Via analyzing the quasi-periodic numerical solutions, the separation mechanism of leading edge flow at low Reynolds number is investigated, and the rules of vortices interaction are summarized. Numerical results indicate that there exists suction spike on airfoil near elliptical leading edge, separation occurs on the effect of strongly adverse pressure gradient of suction spike. Vortices structure including primary vortex, shed vortex and secondary vortex forms on the airfoil surface, its scale varies with time and it is absolutely unsteady. Surface pressure distribution can be used to describe the airfoil boundary layer flow well.
Ye Jian, Zou Zhengping, Lu Lipeng, Yang Lin.Investigation of separation mechanism for airfoil leading edge flow at low Reynolds number[J] JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2004,V30(08): 693-697
½��־. Ҷ�ֻ�ҶƬǰԵ������ǰԵ��״�Ż� . ����:�������պ����ѧ��Դ�붯������ѧԺ,2003 Lu Hongzhi. Flow around the leading edge of turbomachinery blading and improved design for leading edge shapes . Beijing:School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, 2003(in Chinese)