![]() A number of references have been included to allow the reader to study both the older NACA literature and the new airfoil design ideas. Although a new generation of airfoils has emerged as a result of improved understanding of airfoil performance and the ability to design new airfoils using computer methods, the NACA airfoils are still useful in many aerodynamic design applications. Most of the airfoils were based on simple geometrical descriptions of the section shape, although the 6 and 6A series were developed using theoretical analysis and don't have simple shape definitions. A.1 Airfoil Geometry The NACA Airfoils The NACA airfoils were designed during the period from 1929 through 1947 under the direction of Eastman Jacobs at the NACA's Langley Field Laboratory. Section A.1.1 gives some other sources for airfoils. This appendix provides the detailed definition of many of the classic shapes frequently specified in aerodynamics. The design profile chosen is based upon existing literature studies.Īerodynamicists control the flowfield through geometry definition, and are always interested in possible geometric shapes that would be useful in design. The objective is to improve the stability of the airfoil when the flow approaches transonic Mach speeds. The main goal of the proposed paper is to carryout the simulation and analysis of RAE 2822 supercritical airfoil with and without wedge profiles along with the study of aerodynamic characteristics such as Lift and drag coefficients at different Mach numbers. The flow properties such as pressure, temperature and density experience a drastic change upstream and downstream of the generated shock. This shock wave is a type of propagating disturbance which greatly effects the aerodynamic performance of the airfoil. The formation of a shock wave is observed when the free stream approaches a transonic mach number. The present work emphasizes the computation of a supercritical airfoil with and without wedge profiles at different angles of attack and free stream velocities. This led to design changes and optimization of the foil with the help of a cusp like structure added to the trailing edge of the foil. A distinctive supercritical airfoil is found to give inappropriate results at peak operating conditions. The Aerodynamic characteristics of an airfoil play a very important role in terms of design aspects and experimental validation.
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