Aerodynamic design of airfoil for flying wing mars airplane

Takuya Harada, Koji Fujita, Akira Oyama, Hiroya Mamori, Makoto Yamamoto

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)


Aerodynamics optimization of airfoil for flying-wing type Mars airplane is conducted to show tradeoff between maximization of aerodynamic performance and stability requirement. To see the tradeoff between the two objectives, a multiobjective evolutionary algorithm is used where aerodynamic performance of each airfoil is evaluated with a two-dimensional laminar Navier-Stokes flow solver. Some design constraints are applied to obtain feasible airfoil shapes. The obtained Pareto-optimal airfoils show tradeoff between the two design objectives. Analysis of the flow field of the obtained airfoils leads to some useful knowledge in designing airfoil for flying-wing type Mars airplane.

Original languageEnglish
Title of host publicationAIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105241
Publication statusPublished - 2018
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: 2018 Jan 82018 Jan 12

Publication series

NameAIAA Aerospace Sciences Meeting, 2018


OtherAIAA Aerospace Sciences Meeting, 2018
Country/TerritoryUnited States

ASJC Scopus subject areas

  • Aerospace Engineering


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