TY - GEN
T1 - Low-boom design optimization for SST canard-wing-fuselage configuration
AU - Sasaki, Daisuke
AU - Obayashi, Shigeru
PY - 2003
Y1 - 2003
N2 - In this paper, the performance of Adaptive Range Multi-Objective Genetic Algorithm (ARMOGA), which has been developed for reducing a number of function evaluations, is examined by using three analytical test problems. These test problems are also solved by a widely-used Multi-Objective Evolutionary Algorithm (MOEA), NSGA2, and two gradient-based methods, Sequential Quadratic Programming (SQP) and Dynamic Hill Climber (DHC) for comparison. ARMOGA is found to locate a Pareto front with a small number of function evaluations comparable to DHC. To utilize the present ARMOGA, an automated design system of low-boom Supersonic Transport (SST) configuration has been developed. To reduce the sonic boom for supersonic flight effectively with minimizing the drag, SST wing-fuselage configurations equipped with a canard are considered. The resulting system automatically generates unstructured grids around SST canard-wing-fuselage configuration.
AB - In this paper, the performance of Adaptive Range Multi-Objective Genetic Algorithm (ARMOGA), which has been developed for reducing a number of function evaluations, is examined by using three analytical test problems. These test problems are also solved by a widely-used Multi-Objective Evolutionary Algorithm (MOEA), NSGA2, and two gradient-based methods, Sequential Quadratic Programming (SQP) and Dynamic Hill Climber (DHC) for comparison. ARMOGA is found to locate a Pareto front with a small number of function evaluations comparable to DHC. To utilize the present ARMOGA, an automated design system of low-boom Supersonic Transport (SST) configuration has been developed. To reduce the sonic boom for supersonic flight effectively with minimizing the drag, SST wing-fuselage configurations equipped with a canard are considered. The resulting system automatically generates unstructured grids around SST canard-wing-fuselage configuration.
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U2 - 10.2514/6.2003-3432
DO - 10.2514/6.2003-3432
M3 - Conference contribution
AN - SCOPUS:85088181228
SN - 9781624100864
T3 - 16th AIAA Computational Fluid Dynamics Conference
BT - 16th AIAA Computational Fluid Dynamics Conference
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 16th AIAA Computational Fluid Dynamics Conference 2003
Y2 - 23 June 2003 through 26 June 2003
ER -