Low Reynolds aerodynamics and propeller-wing interaction for the Mars airplane

This dissertation is representative of the study the author carried on during his internship in the Department of Space Transportation at the Japan Aerospace Exploration Agency (JAXA) in Sagamihara, Japan. The Mars Airplane is a UA V (Unmanned Air Vehicle) that is currently under development at JAXA...

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Main Author: Daniele, Sirigatti
Other Authors: Daniel Tze How New
Format: Theses and Dissertations
Language:English
Published: 2017
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Online Access:http://hdl.handle.net/10356/72438
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Institution: Nanyang Technological University
Language: English
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spelling sg-ntu-dr.10356-724382023-03-11T16:53:10Z Low Reynolds aerodynamics and propeller-wing interaction for the Mars airplane Daniele, Sirigatti Daniel Tze How New School of Mechanical and Aerospace Engineering DRNTU::Engineering::Aeronautical engineering This dissertation is representative of the study the author carried on during his internship in the Department of Space Transportation at the Japan Aerospace Exploration Agency (JAXA) in Sagamihara, Japan. The Mars Airplane is a UA V (Unmanned Air Vehicle) that is currently under development at JAXA, within the framework of the MELOSI (Mars Exploration with a Lander-Orbiter Synergy) 2020/2030 program. A JAXA in-house CFD (Computational Fluid Dynamics) Structured code was used to investigate the behavior of a NACAOO 12 airfoil for the Mars Airplane at low Reynolds numbers (4xl04 ), in order to compare the results with existing experimental data. A structured C-Type mesh generator was prograInmed in Fortran90 to build a grid topology suitable for the study. First tests were run on a 2D mesh to assess the suitability of the mesh topology to the CFD solver. Then, a series of 3D LES (Large Eddy Simulation) computations were run at different angles of attack and grid resolutions as mesh sensitivity study, to find the best compromise between solution accuracy and computational time. Subsequently, an Actuator Blade Model for the propeller was investigated and partially implemented. Finally, the CFD results were compared with wind tunnel tests performed in the Low speed wind tunnel at the Institute of Fluid Science at Tohoku University, Japan. The 3D LES results showed good accordance with the experimental data without propeller, however due to time constrains, it was not possible to develop a working Actuator Blade Model to properly simulate the propeller-wing interaction. Nevertheless, a literature review of past and present actuator blade models are thoroughly discussed in the present study as basis for future developments. Master of Science (Aerospace Engineering) 2017-07-17T07:49:25Z 2017-07-17T07:49:25Z 2017 Thesis http://hdl.handle.net/10356/72438 en 64 p. application/pdf
institution Nanyang Technological University
building NTU Library
continent Asia
country Singapore
Singapore
content_provider NTU Library
collection DR-NTU
language English
topic DRNTU::Engineering::Aeronautical engineering
spellingShingle DRNTU::Engineering::Aeronautical engineering
Daniele, Sirigatti
Low Reynolds aerodynamics and propeller-wing interaction for the Mars airplane
description This dissertation is representative of the study the author carried on during his internship in the Department of Space Transportation at the Japan Aerospace Exploration Agency (JAXA) in Sagamihara, Japan. The Mars Airplane is a UA V (Unmanned Air Vehicle) that is currently under development at JAXA, within the framework of the MELOSI (Mars Exploration with a Lander-Orbiter Synergy) 2020/2030 program. A JAXA in-house CFD (Computational Fluid Dynamics) Structured code was used to investigate the behavior of a NACAOO 12 airfoil for the Mars Airplane at low Reynolds numbers (4xl04 ), in order to compare the results with existing experimental data. A structured C-Type mesh generator was prograInmed in Fortran90 to build a grid topology suitable for the study. First tests were run on a 2D mesh to assess the suitability of the mesh topology to the CFD solver. Then, a series of 3D LES (Large Eddy Simulation) computations were run at different angles of attack and grid resolutions as mesh sensitivity study, to find the best compromise between solution accuracy and computational time. Subsequently, an Actuator Blade Model for the propeller was investigated and partially implemented. Finally, the CFD results were compared with wind tunnel tests performed in the Low speed wind tunnel at the Institute of Fluid Science at Tohoku University, Japan. The 3D LES results showed good accordance with the experimental data without propeller, however due to time constrains, it was not possible to develop a working Actuator Blade Model to properly simulate the propeller-wing interaction. Nevertheless, a literature review of past and present actuator blade models are thoroughly discussed in the present study as basis for future developments.
author2 Daniel Tze How New
author_facet Daniel Tze How New
Daniele, Sirigatti
format Theses and Dissertations
author Daniele, Sirigatti
author_sort Daniele, Sirigatti
title Low Reynolds aerodynamics and propeller-wing interaction for the Mars airplane
title_short Low Reynolds aerodynamics and propeller-wing interaction for the Mars airplane
title_full Low Reynolds aerodynamics and propeller-wing interaction for the Mars airplane
title_fullStr Low Reynolds aerodynamics and propeller-wing interaction for the Mars airplane
title_full_unstemmed Low Reynolds aerodynamics and propeller-wing interaction for the Mars airplane
title_sort low reynolds aerodynamics and propeller-wing interaction for the mars airplane
publishDate 2017
url http://hdl.handle.net/10356/72438
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