STUDY OF THE INFLUENCE OF LEADING EDGE ROTATING CYLINDER ON THE PERFORMANCE OF A SYMMETRIC AEROFOIL

Abstract

This research dealt with moving surface boundary layer control, applied to NACA 0018 aerofoil both by simulation and experiment. The moving surface was provided by a rotating cylinder placed at the leading edge of the aerofoil. In aeronautics, Reynolds number 105 constitutes an important speed regime as many unmanned aerial vehicle operates in this regime. But little work was done in this field. Thus, this research aims for investigation of aerofoil performance having rotating cylinder at the leading edge in the Reynolds number range of 105 regime. For conducting this research on a symmetric aerofoil, NACA 0018 was chosen. Experimental data on NACA 0018 aerofoil at Reynolds number 2.4 X 105 were obtained from existing literature. The set of data was taken and simulations were done on the same aerofoil with different models like k-ω SST, Spalart Almaras. It was found that data obtained by k-ω SST model were close to experimental data. Thus in the present investigation simulations were done using this model in ANSYS. Performance of NACA 0018 were investigated and data from the modified NACA 0018 aerofoil was obtained at four different Reynolds number 1.4 X 105 to 2.8 X 105 with zero rpm and five other rpm starting from 3000 to 5000 with the interval of 500. Results obtained through experiment were then compared with the simulation data of NACA 0018 aerofoil. This comparison showed that at lower Reynolds number (at 1.4 X 105 & 1.85 X 105) stall was delayed as well as maximum lift coefficient was increased while at Reynolds number 2.3 X 105 stall was delayed without any increment in maximum lift coefficient. Finally at Reynolds number 2.8 X 105 stall was little delayed with a slight decrease in maximum lift coefficient because of increase in velocity ration as well as vibration.