Kenichi RINOIE

Professor, Department of Aeronautics and Astronautics

Research Fields

Aircraft Design, Aerodynamics of Aircraft, Separated Flow Aerodynamics

Lectures

for undergraduate students

  • Aircraft Design 1
  • Aircraft Design 2
  • Aerospace System Planning & Design (in charge of Aircraft Design)

for postgraduate students

  • Mechanics of Viscous and Turbulent Flow
  • Special Lectures on Aircraft Design
  • Experimental Fluid Mechanics 1



Taro IMAMURA

Associate Professor, Department of Aeronautics and Astronautics

Research Fields

Computational Fluid Dynamics, Computational Aeroacoustics, Low Speed Wind Tunnel Testing

Research Topics

1.Development of Compressible Flow Simulation Code using Cartesian Mesh Method


The basis of Computational Fluid Dynamics (CFD) was formed during 1980-90s. However, it was not until recently that CFD was used in actual aircraft design and its usage is limited mainly to the estimation of cruising performances. A few problems must be addressed to employ CFD for estimating take-off & landing performances, especially when high lift devices and ailerons are activated. Studies for prediction of aircraft noise are also being conducted in recent years. Development of CFD tools applicable to these kinds of problems are ongoing.

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Pressure distribution of an aircraft (transonic)
Sound radiated from unsteady flow around a 2D column
 

2.Method for Prediction and Reduction of Aircraft Noise


It is known that the major noise sources of an aircraft are engines and airframe, but each of them has different characteristics. For example, jet noise decreases with speed, but aerodynamic noise increases. Noises are related to various factors such as flight path, operating system, weather and geographical features. We aim to contribute to innovative aircraft design by developing noise prediction tools considering all these characteristics and employing it in the early stage of the design.
The figures show shielding effect of V-tails, when engine (noise source) is mounted above the fuselage.

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3.Development of Dynamic Wind Tunnel Facilities


The objective of this study is to develop dynamic wind tunnel testing methods that can provide with dynamic stability derivatives in the early stage of aircraft design. Dynamic wind tunnel facilities used to be huge due to the sizes of model aircraft, drive system, measurement system etc. As a consequence, dynamic wind tunnel facilities weren’t frequently used in conceptual aircraft design. Although measurement systems to evaluate aerodynamic performance of an aircraft used to be very expensive, we aim to merge aerodynamics and flight control using MEMS (Micro Electro Mechanical Systems) sensors, which are very small, light-weight, cheap, and less power consuming.
The picture on the left shows the facility to measure aerodynamic forces varying AoA. The figure on the right shows the result of flight simulation coupled with equation of motion using the facility.

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Lectures

for undergraduate students

  • Dynamics of Flight 1
  • Aerospace System Planning & Design (in charge of Aircraft Design)

for postgraduate students

  • Special Lectures on Aircraft Design
  • Aerodynamic Design of Aircraft
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