Aerodynamic analysis of supercritical airfoil

Abstract

The study of aero structures and its stability is gaining greater importance due the exponential advances in the aeronautical field. The design of aircraft wings and its aerodynamic analysis is crucial for the design of aircrafts. The work focuses on the aerodynamic analysis of an aircraft wing subjected to a flow in the transonic regime. A supercritical airfoil is used for the design, as these types of airfoils are usually used in the transonic region. Aerodynamic analysis including the pressure analysis, pressure coefficient analysis and the variation of lift and drag with the Mach number is investigated. The effect of these parameters with the angle of attack is also studied. The results indicate that the pressure at the leading edge of the airfoil is maximum and an increase of lift is achieved with an increase in the angle of attack at a particular Mach number. The Mach number for a maximum lift is also noted. The pressure coefficient analysis indicates an onset of a pressure coefficient drop towards the trailing edge of the wing.