In an effort to further improve upon the latest advancements made in aerodynamic shape optimization procedures, a systematic study is performed to examine several current solution methodologies as applied to various aspects of the optimization procedure. It is demonstrated that preconditioned conjugate gradient-like methodologies dramatically decrease the computational efforts required for such procedures. The design problem investigated is the shape optimization of the upper and lower surface of an intially symmetric (NACA 0012) airfoil in inviscid transonic flow and at zero degrees angle of attack. The complete surface shape is represented using a Bezier-Bernstein polynomial. The present optimization method is demonstrated to automatically obtain supercritical airfoil shapes over a variety of freestream Mach numbers. Furthermore, the best optimization strategy examined resulted in a factor of 8 decrease in computational time as well as a factor of 4 decrease in memory over the most efficient strategies in current use.
Aerodynamic shape optimization using preconditioned conjugate gradient methods
Arodynamische Formoptimierung mittels vorbereiteter konjugater Gradientenmethode
AIAA Journal ; 32 , 11 ; 2145-2152
1994
8 Seiten, 6 Bilder, 2 Tabellen, 27 Quellen
Aufsatz (Zeitschrift)
Englisch
Aerodynamic Shape Optimization Using Preconditioned Conjugate Gradient Methods
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