Aerodynamic characteristics of mars airplane airfoils with control surface in propeller slipstream

Kakeru Kurane, Kenta Uechi, Koichi Takahashi, Koji Fujita, Hiroki Nagai

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

4 Citations (Scopus)

Abstract

Aerodynamic characteristics of airfoils in a propeller slipstream were investigated at low Reynolds number. The effects of a propeller slipstream on control surface effectiveness were clarified by aerodynamic force measurement and the Particle Image Velocimetry (PIV) measurement. The tests were conducted using the small low-turbulence wind tunnel in the Institute of Fluid Science, Tohoku University, at the chord Reynolds number of 3.0×104. The airfoils tested were the Ishii and T1-2 airfoils, the two main candidates for the Japanese Mars airplane. Two configurations were used in the testing, one configuration with a propeller set in front of the wing and one configuration without a propeller to be used as a baseline. For the case without the propeller, the Ishii airfoil control surface effectiveness increased according to the deflection angle. However, the effectiveness of the T1-2 airfoil did not increase at certain angles of attack. When the propeller was set, the effectiveness increased according to the deflection angle for both airfoils. These results indicate that a propeller would have a positive effect on controllability of a Mars airplane.

Original languageEnglish
Title of host publicationAIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Edition210059
ISBN (Print)9781624105241
DOIs
Publication statusPublished - 2018 Jan 1
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: 2018 Jan 82018 Jan 12

Publication series

NameAIAA Aerospace Sciences Meeting, 2018
Number210059

Other

OtherAIAA Aerospace Sciences Meeting, 2018
Country/TerritoryUnited States
CityKissimmee
Period18/1/818/1/12

ASJC Scopus subject areas

  • Aerospace Engineering

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