Gustavo Fujiwara

Gustavo Fujiwara
University of Washington Seattle | UW · Department of Aeronautics and Astronautics

PhD Student

About

22
Publications
27,182
Reads
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279
Citations
Introduction
Gustavo Fujiwara currently works at the Department of Aeronautics and Astronautics, University of Washington Seattle. Gustavo does research in Aerospace Engineering and Aeronautical Engineering. Their current project is 'Multidisciplinary Design Optimization of Flexible Aircraft with Morphing Wings.'
Additional affiliations
September 2014 - present
University of Washington Seattle
Position
  • Research Assistant
May 2014 - November 2017
NASA Ames Research Center
Position
  • Graduate Research Intern
August 2012 - June 2014
University of Illinois, Urbana-Champaign
Position
  • Research Assistant
Education
September 2014 - February 2019
University of Washington Seattle
Field of study
  • Aeronautics and Astronautics
August 2012 - August 2014
University of Illinois, Urbana-Champaign
Field of study
  • Aerospace Engineering
February 2006 - December 2011
University of São Paulo
Field of study
  • Mechanical Engineering

Publications

Publications (22)
Conference Paper
Full-text available
A particular field of aerospace engineering is dedicated to the study of aircraft that are so energetically efficient, that the power produced by a human being enables it to takeoff and maintain sustained flight without any external or stored energy. These aircraft are known as Human-Powered Aircraft (HPA). The objective of the present work is to d...
Article
The variable-camber continuous trailing-edge flap is a novel control surface technology designed to serve as an aeroelastic wing shaping control device. Capable of minimizing drag throughout an aircraft flight envelope, use of the variable-camber continuous trailing-edge flap technology is examined on a flexible-wing transport aircraft configuratio...
Conference Paper
Full-text available
A significant portion of low-speed aircraft design is influenced by ice formation and its impact on aerodynamic performance and flying qualities. Computational fluid dynamic codes and icing simulation tools play a key role in predicting icing effects and are maturing to levels that aircraft manufacturers are proposing their use in icing certificati...
Article
A comparison of computational and experimental ice accretions generated on three swept-wing models in the NASA Glenn Icing Research Tunnel is presented. The wind tunnel models span floor to ceiling and present the same full-scale leading edges of three different spanwise wing stations of the 65%-scale modern commercial aircraft known as the Common...
Article
Hybrid-wing models are those that present the same leading-edge geometry of the full-scale aircraft wing and a redesigned aft section of reduced chord, such that models can be tested inside an icing wind tunnel. When properly designed, these models reproduce the full-scale flowfield and ice accretions on the leading edge, with reduced tunnel blocka...
Article
The certification of modern commercial aircraft requires manufacturers to demonstrate flight safety under various scenarios, including icing conditions. Although computational tools play a key role in icing-related aircraft design and certification, icing wind-tunnel testing remains an important part of the process. The size of models that can be t...
Technical Report
Full-text available
This report presents key results from the first 2 years of a program to develop experimental icing simulation capabilities for full-scale swept wings. This investigation was undertaken as part of a larger collaborative research effort on ice accretion and aerodynamics for large-scale swept wings. Ice accretion and the resulting aerodynamic effect o...
Conference Paper
Full-text available
A numerical study of how to simulate heavy atmospheric particle collisions with a 38-m, 1.5-MW horizontal axis wind turbine blade is discussed. Two types of particles were considered, namely hailstones and rain drops. Computations were performed by using a two-dimensional inviscid flowfield solver along with a particle position predictor code. Thre...
Conference Paper
Full-text available
A 3D swept hybrid wing design method using hybrid airfoils is presented for the purpose of icing wind tunnel testing of large commercial aircraft. Hybrid airfoils are those that present the same leading-edge geometry of the full-scale aircraft wing with a redesigned truncated aft section, to reproduce full-scale flowfield and ice accretion with red...
Conference Paper
Full-text available
Modern commercial aircraft wings are far too large to be tested full-scale in existing icing wind tunnels and ice accretion scaling methods are not practical for large scale factors. Thus the use of hybrid scaling techniques, maintaining full-scale leading-edges and redesigned aft sections, is an attractive option for generating full-scale leading-...

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Projects

Projects (2)
Project
Application of active aeroelastic wing shaping control during flight to reduce wing design loads, prevent adverse aeroelastic effects that can occur for highly-flexible aircraft, and improve passenger ride comfort.