Aerodynamic Optimization Using Simulated Annealing and its Variants
|International Journal of Engineering Trends and Technology (IJETT)||
|© 2011 by IJETT Journal|
|Year of Publication : 2011|
|Authors : R. Mukesh, Dr. K. Lingadurai
R. Mukesh, Dr. K. Lingadurai. "Aerodynamic Optimization Using Simulated Annealing and its Variants". International Journal of Engineering Trends and Technology (IJETT),V2(3):73-77 Nov to Dec 2011. ISSN:2231-5381. www.ijettjournal.org. Published by Seventh Sense Research Group.
Nowadays engineering analysis relies heavily on computer - based solution algorithms to investigate the performance of an engineering system. Computational fluid dynamics (CFD) is one of the computer - based solution methods which are more widely employed in aerospace engineering. The computational power and time required to carry out the analysis increases as the fidelity of the analysis increases. Aerodynamic shape optimization has become a vital part of aircraft design in the recent years. Generally i f we want to optimize an airfoil we have to describe the airfoil and for that, we need to have at least hundred points of x and y co - ordinates. It is really difficult to optimize airfoils with this large number of co - ordinates. Nowadays many different sche mes of parameter sets are used to describe general airfoil such as B - spline, Hicks - Henne Bump function, PARSEC etc. The main goal of these parameterization schemes is to reduce the number of needed parameters as few as possible while controlling the impor tant aerodynamic features effectively. Here the work has been done on the PARSEC geometry representation method. The objective of this work is to introduce the knowledge of describing general airfoil using twelve parameters by representing its shape as a p olynomial function. And also we have introduced the concept of Simulated Annealing (SA) and Simplex - Simulated Annealing (SIMPSA) to optimize the aerodynamic characteristics of a general airfoil for specific conditions. A MATLAB program has been developed t o implement PARSEC, Panel Technique, SA and SIMPSA . This program has been tested for a standard NACA 2411 airfoil and optimized to improve its coefficient of lift. Pressure distribution and co - efficient of lift for airfoil geometries has been calculated us ing panel method. NACA 2411 airfoil has been generated using PARSEC and optimized for 5.0 de g angle of attack using SA and SIMPSA .
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Aerodynamic Shape Optimization, Genetic Algorithm, Parametric Section, SA , SIMPSA