A Genetic Algorithm (GA) has been applied to optimize a transonic wing shape for generic transport aircraft. A three-dimensional compressible Navier-Stokes (N-S) solver is used to evaluate aerodynamic performance. The N-S evaluation is parallelized on Numerical Wind Tunnel (NWT) at National Aerospace Laboratory in Japan, a parallel vector machine with 166 processing elements. Designed wings show a tradeoff between an increase of the airfoil thickness driven by a structural constraint and a reduction of the wave drag produced by a shock wave. The present result indicates that GA has found a best feasible solution in the given design constraints.
|出版ステータス||Published - 1997 1 1|
|イベント||13th Computational Fluid Dynamics Conference, 1997 - Snowmass Village, United States|
継続期間: 1997 6 29 → 1997 7 2
|Other||13th Computational Fluid Dynamics Conference, 1997|
|Period||97/6/29 → 97/7/2|
ASJC Scopus subject areas