Home – Home – Jornals – Journal of Applied Mechanics and Technical Physics 2026 number 3

Results of an experimental study on the effectiveness of controlling incompressible turbulent flow over an asymmetric Clark Z airfoil using a perforated surface are presented. The perforated surface consists of an array of cylindrical cavities or through-holes with variable geometric parameters. The cavities are located on the lower surface of the wing, most of which is exposed to zero-pressure-gradient flow. The study is conducted over a chord Reynolds number range of Re_c = (0.601-1.324) × 10⁶ at an angle of attack of 3.6°, corresponding to a momentum thickness Reynolds number range at the perforated surface inlet Re_θ = 527-992. Particular attention is given to a previously unexplored analysis of the potential for reducing the aerodynamic drag of the airfoil under these conditions. It is shown that none of the perforated surface configurations under study provides a drag reduction within the experimental uncertainty.