منابع مشابه
A Study on Airfoil Design for Future Mars Airplane
An optimum airfoil design for future Mars airplane for Mars exploration is obtained by evolutionary computation coupled with a two-dimensional Reynolds-averaged Navier-Stokes solver. The optimized airfoil design is also compared with other airfoil designs optimized at different Reynolds number or at different Mach number to discuss Reynolds number and Mach number effects on airfoil design. Thes...
متن کاملAirfoil Design Optimization for Airplane for Mars Exploration
Aerodynamic design optimization of an airfoil for the Mars exploration airplane has been demonstrated by using an evolutionary algorithm. The adaptive range genetic algorithm is used for efficient and robust design optimization. Two-dimensional Navier-Stokes solver is used for accurate aerodynamic performance evaluation. The present computation is parallelized on the SX-6 vector computers in In...
متن کاملConceptual Blending and Airplane Navigation
Fauconnier and Turner’s conceptual blending theory (1998) has been used to analyze many types of cognitive phenomena, particularly the role blending plays in language comprehension. In this paper we illustrate how blending also has a role in mediating expert performance, such as understanding the meaning of a chart or a navigation display. Pilots use blends to assess flight situations, predict ...
متن کاملRobust Aerodynamic Design of Mars Exploratory Airplane Wing with a New Optimization Method
The use of airplanes for Mars exploration is a new and attractive approach because it provides high resolution power and large spatial coverage. However, it is also a challenging approach in engineering viewpoint. Mars airplanes are required to fly in lower Reynolds number and higher subsonic Mach number conditions due to thinner atmosphere and smaller speed of sound on the Mars, compared to ty...
متن کاملMulti-Objective Six Sigma Approach Applied to Robust Airfoil Design for Mars Airplane
A new optimization approach for robust design, design for multi-objective six sigma (DFMOSS) has been developed and applied to robust aerodynamic airfoil design for Mars exploratory airplane. The present robust aerodynamic airfoil design optimization using DFMOSS successfully showed the trade-off information between maximization and robustness improvement in aerodynamic performance by a single ...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
سال: 2012
ISSN: 1884-0485
DOI: 10.2322/tastj.10.te_5