Viscous Flow Computations of Aircraft with Changing Control Surface Deflection Using Unstructured Grids

2003 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Yasushi Ito ◽  
Kazuhiro Nakahashi ◽  
Kisa Matsushima ◽  
Toshiyuki Iwamiya
Keyword(s):  
Viscous Flow ◽  
Unstructured Grids ◽  
Control Surface ◽  
Surface Deflection

Viscous flow computations of aircraft with changing control surface deflection using unstructured dynamic meshes

2006 ◽  
Vol 52 (8) ◽  
pp. 925-940 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Yasushi Ito ◽  
Kazuhiro Nakahashi ◽  
Kisa Matsushima ◽  
Toshiyuki Iwamiya
Keyword(s):  
Viscous Flow ◽  
Control Surface ◽  
Surface Deflection

Overset Unstructured Grids Method for Viscous Flow Computations

AIAA Journal ◽  
2006 ◽  
Vol 44 (7) ◽  
pp. 1617-1623 ◽  
Author(s):  
Fumiya Togashi ◽  
Yasushi Ito ◽  
Kazuhiro Nakahashi ◽  
Shigeru Obayashi
Keyword(s):  
Viscous Flow ◽  
Unstructured Grids

Overset Unstructured Grids Method for Viscous Flow Computations

2003 ◽  
Author(s):  
Fumiya Togashi ◽  
Yasushi Ito ◽  
Kazuhiro Nakahashi ◽  
Shigeru Obayashi
Keyword(s):  
Viscous Flow ◽  
Unstructured Grids

Composite Wing Flutter Speed and Frequency due to Variable Control Surface Deflection in Low Speed Wind Tunnel

2013 ◽  
Vol 390 ◽  
pp. 3-7
Author(s):  
Muhammad Iyas Mahzan ◽  
Sallehuddin Muhamad ◽  
Sa’ardin Abdul Aziz ◽  
Mohamed Sukri Mat Ali
Keyword(s):  
Wind Tunnel ◽  
Dynamic Instability ◽  
Wind Tunnel Test ◽  
Control Surface ◽  
Wing Flutter ◽  
Flutter Speed ◽  
Surface Deflection ◽  
Relationship Of ◽  
Low Speed Wind Tunnel ◽  
The Relationship

Flutter is a dynamic instability problem represents the interaction among structural, aerodynamic, elastic and inertial forces and occurred when the energy is continuously transformed by the surrounding fluids to a flying structure in the form of kinetic energy. The study was conducted to investigate the relationship of the control surface deflection angle to the flutter speed and the flutter frequency. A wind tunnel test was performed using a flat plate wing made of composite material. It was found that by deflecting the control surface up to 45°, the flutter speed reduced almost linearly from 35.6 m/s to 22.7 m/s. The flutter frequency greatly reduced from 48 Hz without the control surface deflected to 34 Hz with the control surface deflected at 15°. After 15° deflection up to 45°, the flutter frequency reduced almost linearly.

The adaptation of unstructured grids for transonic viscous flow simulation

1997 ◽  
Vol 25 (3-4) ◽  
pp. 199-218 ◽  
Author(s):  
M.J. Marchant ◽  
N.P. Weatherill ◽  
O. Hassan
Keyword(s):  
Viscous Flow ◽  
Unstructured Grids ◽  
Flow Simulation

Simulation of Aircraft Response to Control Surface Deflection Using Unstructured Dynamic Grids

2005 ◽  
Vol 42 (2) ◽  
pp. 340-346 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Fumiya Togashi ◽  
Kazuhiro Nakahashi ◽  
Kisa Matsushima ◽  
Takuma Kato
Keyword(s):  
Control Surface ◽  
Surface Deflection
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