Experimental Analysis of Implementing Roughness on NACA 0018 Airfoil

Sie sind hier: Homepage > Suche

Experimental Analysis of Implementing Roughness on NACA 0018 Airfoil

Livya, E. / Sai Anirudh, R. / Vignesh, V. / Prasannavenkatesh, B. / Nadaraja Pillai, S.

Abstract The aerodynamic characteristics of introducing roughness on an airfoil surface are measured in a subsonic wind tunnel. The roughness is introduced on one-fourth of the chord length, and experiments are conducted. In conventional airfoils, there is a substantial decrease in the coefficient of lift once the critical angle of attack is attained. This affects the aerodynamic performance of aircraft. Though there are methods to resolve this, there are drawbacks too, such as an increase in takeoff weight, which are detrimental to the overall performance. To avoid such drawbacks and still achieve delayed stalling, roughness is introduced on the airfoil surface. The pressure is measured for various angles of attack from 2° to 18° in steps of 2°, for inlet velocities of 25, 35, and 45 m/s. A delay in stalling has been achieved, from 8° to 12°, but there is a fall in the lift coefficient compared to that of a conventional airfoil, due to the addition of skin friction to the airfoil surface.