Author(s)

Z. Mahmood, M.K. Khan, W.J. Scale & H.H. Bruun

Abstract

This paper describes results obtained from a comparative experimental and numerical investigation of air flow over a NACA 4412 high-lift aerofoil with and without a flap section. The experimental study focused on the flow over the top part of the aerofoil with particular interest in the separation region near trailing edge. Measurements were carried out with Hot-wire anemometry. Two methods were used: a) a conventional stationary hot-wire probe and b) a flying hot-wire probe. The same X hot-wire probe was used for both types of measurements, with the probe locked in position for the stationary probe data. Comparative numerical results have been obtained by solving the time- averaged Navier-Stokes equations for a turbulent flow, using the conditions similar to the experi

Keywords