DocumentCode
518354
Title
Notice of Retraction
Aerodynamic shape optimization using computer mapping of natural evolution process
Author
Selvakumar, U. ; Mukesh, P.R.
Author_Institution
Dept. of Aeronaut. Eng., Bannari Amman Inst. of Technol., Sathyamangalam, India
Volume
5
fYear
2010
fDate
16-18 April 2010
Abstract
Notice of Retraction
After careful and considered review of the content of this paper by a duly constituted expert committee, this paper has been found to be in violation of IEEE´s Publication Principles.
We hereby retract the content of this paper. Reasonable effort should be made to remove all past references to this paper.
The presenting author of this paper has the option to appeal this decision by contacting TPII@ieee.org.
Generally in order to describe the geometry of a general airfoil we need to have at least hundred points of x and y coordinates. It is really difficult to optimize airfoils with this large number of co-ordinates. Nowadays many different schemes of parameter sets are used to describe the geometry of general airfoil like Bezier, B-spline, Hicks-Henne Bump function, PARSEC etc. The main goal of these methods is to reduce the number of design parameters as few as possible while controlling the important aerodynamic features effectively. In this paper, the problem of finding the optimized locations of PARSEC parameters which describe the geometry of general airfoil to improve its aerodynamic performance is formulated as an optimization problem and solved using the computer mapping of the natural evolution process called genetic algorithm. As an example, NACA 2411 airfoil is selected and optimized to improve its co-efficient of lift for 5.0 deg angle of attack.
After careful and considered review of the content of this paper by a duly constituted expert committee, this paper has been found to be in violation of IEEE´s Publication Principles.
We hereby retract the content of this paper. Reasonable effort should be made to remove all past references to this paper.
The presenting author of this paper has the option to appeal this decision by contacting TPII@ieee.org.
Generally in order to describe the geometry of a general airfoil we need to have at least hundred points of x and y coordinates. It is really difficult to optimize airfoils with this large number of co-ordinates. Nowadays many different schemes of parameter sets are used to describe the geometry of general airfoil like Bezier, B-spline, Hicks-Henne Bump function, PARSEC etc. The main goal of these methods is to reduce the number of design parameters as few as possible while controlling the important aerodynamic features effectively. In this paper, the problem of finding the optimized locations of PARSEC parameters which describe the geometry of general airfoil to improve its aerodynamic performance is formulated as an optimization problem and solved using the computer mapping of the natural evolution process called genetic algorithm. As an example, NACA 2411 airfoil is selected and optimized to improve its co-efficient of lift for 5.0 deg angle of attack.
Keywords
aerodynamics; aerospace components; computational geometry; design engineering; genetic algorithms; mechanical engineering computing; NACA 2411 airfoil; PARSEC parameters; aerodynamic shape optimization; airfoil geometry; computer mapping; design parameters; genetic algorithm; natural evolution process; Aerodynamics; Aerospace engineering; Automotive components; Design optimization; Genetic algorithms; Geometry; Polynomials; Shape control; Spline; Surface treatment; Aerodynamic Shape Optimization; Genetic Algorithm; MDO; Parametric Section;
fLanguage
English
Publisher
ieee
Conference_Titel
Computer Engineering and Technology (ICCET), 2010 2nd International Conference on
Conference_Location
Chengdu
Print_ISBN
978-1-4244-6347-3
Type
conf
DOI
10.1109/ICCET.2010.5486070
Filename
5486070
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