The linear stability based on Orr-Sommerfeld equations and the eN method was employed to determine the onset and control of transition over VFW-VF-2 and NACA653-018 aerofoil sections. For the VFW-VF-2 aerofoil, the effects of active suction on shock-boundary layer interaction were investigated. An enhanced lift to drag ratio was obtained for incidence angles below 6 degrees using suction coefficient as tiny as 0.0006. A parametric study were conducted to show the effects of the suction slot location, suction inclination angle and the extent of sucked flow through slots for flows around the NACA653-018 aerofoil. It was observed that transition was delayed regardless of suction positions. However, maximum delay in transition occurred when the sucked region was located between a critical point and the transition point. For all the cases studied here, lift to drag ratio was increased using active surface suction.
Control of Transition over Aerofoil Surfaces using Active Suction
M. Ahmadi-BaloutakiRelated information
1 Department of Mechanical Engineering, University of Windsor, Ontario N9B 3P4, Canada
, A. SedaghatRelated information2 Department of Mechanical Engineering, Isfahan University of Technology, Isfahan 84156-8311, Iran
, M. SaghafianRelated information2 Department of Mechanical Engineering, Isfahan University of Technology, Isfahan 84156-8311, Iran
, M. BadriRelated information3 Research Institute for Subsea Science & Technology, Isfahan University of Technology, Isfahan 84156-8311, Iran
Published Online: March 20, 2014
Abstract