Robust Aerodynamic Airfoil Design Optimization against Wind Variations for Mars Exploratory Airplane
- Paper number
IAC-06-A3.P.3.07
- Author
Mr. Koji Shimoyama, University of Tokyo, Japan
- Coauthor
Dr. Akira Oyama, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan
- Coauthor
Prof. Kozo Fujii, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan
- Year
2006
- Abstract
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 typical commercial Earth airplanes. The design concepts for Mars airplanes flying in such unique conditions have not been established sufficiently yet. Therefore, it is required to search better design of Mars airplane in wide design space and establish a new design concept for Mars airplanes. In addition, it is well known that there exist large wind variations on the Mars. Such wind variations may lead to drastic deterioration in performance, and thus failure in expected Mars exploratory mission. Therefore, it is also required to consider not only the optimality but also the robustness of performance against wind variations for more realistic and reliable design of Mars airplane. In this paper, robust aerodynamic airfoil design optimizations for Mars exploratory airplane considering the effects of wind variations were carried out by using a robust design optimization approach “design for multi-objective six sigma (DFMOSS)” coupled with the CFD simulation, and realistic design information about the trade-off relation between the optimality and the robustness of aerodynamic performance of Mars exploratory airplane was discussed based on the numerical results. The present optimizations successfully revealed strong trade-off information between the optimality and the robustness of aerodynamic performance. These results indicated that an airfoil with large camber can improve the robustness in lift to drag ratio against the variation of flight Mach number, an airfoil with larger curvature in the front part can improve the robustness in pitching moment against the variation of flight Mach number, and an airfoil with blunter leading edge can improve the robustness of lift to drag ratio against the variation of angle of attack.
- Abstract document
- Manuscript document
IAC-06-A3.P.3.07.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.