Experimental and rans analysis of full mars airplane configurations

Shota Taniguchi, Akira Oyama, Masato Okamoto, Masayuki Anyoji, Koji Fujita, Hiroki Nagai

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

Abstract

To evaluate Reynolds-averaged Navier-Stokes (RANS) simulation and to understand control surface effects in low Reynolds number flow condition (60,000), wind tunnel experiment and RANS simulation results of the full configuration of a Mars airplane with control surface deflection are obtained. The RANS analysis is conducted using FaSTAR, that bases on Menter’s k-ω shear-stress transport (SST) model with γ-Reθ model for turbulence model. The lift coefficient and pitching moment coefficient of the airplane with zero control surface deflection predicted by the RANS simulation and those measured by the wind tunnel experiment show qualitatively good agreement while those obtained by the RANS simulation are lower quantitatively. As for the elevator effects, the RANS simulation and experiment results show good agreement. Aileron effects obtained by the RANS simulation and experiment also show good agreement at side slip angle of 0 degree, while they have discrepancy in the flow conditions with sideslip angle. The rudder effects obtained by the RANS simulation and experiment show qualitatively good agreement except for the cases at very large side slip angle.

Original languageEnglish
Title of host publicationAIAA Scitech 2020 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages1-14
Number of pages14
ISBN (Print)9781624105951
DOIs
Publication statusPublished - 2020
EventAIAA Scitech Forum, 2020 - Orlando, United States
Duration: 2020 Jan 62020 Jan 10

Publication series

NameAIAA Scitech 2020 Forum
Volume1 PartF

Conference

ConferenceAIAA Scitech Forum, 2020
CountryUnited States
CityOrlando
Period20/1/620/1/10

ASJC Scopus subject areas

  • Aerospace Engineering

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