Hydrodynamic comparison of shunt and endoscopic third ventriculostomy in adult hydrocephalus using in vitro models and fluid-structure interaction simulation

2021 ◽  
pp. 106049
Author(s):  
Seifollah Gholampour ◽  
Mehrnoosh Bahmani
Keyword(s):  
Endoscopic Third Ventriculostomy ◽  
Fluid Structure Interaction ◽  
In Vitro Models ◽  
Third Ventriculostomy ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Interaction Simulation

Fluid-structure interaction simulation of artificial textile reinforced aortic heart valve: Validation with an in-vitro test

2018 ◽  
Vol 78 ◽  
pp. 52-69 ◽  
Author(s):  
Deepanshu Sodhani ◽  
Stefanie Reese ◽  
Andrey Aksenov ◽  
Sinan Soğanci ◽  
Stefan Jockenhövel ◽  
...  
Keyword(s):  
Heart Valve ◽  
Fluid Structure Interaction ◽  
In Vitro Test ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Aortic Heart Valve ◽  
Vitro Test ◽  
Interaction Simulation

scholarly journals Fluid–structure interaction simulation on flight performance of a dragonfly wing under different pterostigma weights

2021 ◽  
Vol 37 ◽  
pp. 216-229
Author(s):  
Yung Jeh Chu ◽  
Poo Balan Ganesan ◽  
Mohamad Azlin Ali
Keyword(s):  
Optimization Design ◽  
Fluid Structure Interaction ◽  
Spatial Location ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Dragonfly Wing ◽  
Interaction Simulation ◽  
Wing Performance ◽  
Drag Ratio ◽  
Lift To Drag Ratio

Abstract The dragonfly wings provide insights for designing an efficient biomimetic micro air vehicle (BMAV). In this regard, this study focuses on investigating the effect of the pterostigma weight loading and its spatial location on the forewings of dragonfly by using the fluid–structure interaction simulation. This study also investigates the effect of change in the wing elasticity and density on the wing performance. The forewing, which mimics the real dragonfly wing, is flat with a 47.5 mm span and a 0.4 mm thickness. The wing was set to cruise at 3 m/s with a constant flapping motion at a frequency of 25 Hz. This study shows that a small increase of pterostigma loading (11% of wing weight) at the tip of the wing significantly improves the lift to drag ratio, CL/CD, which has 129.16% increment in comparison with no loading. The lift to drag ratio depends on the pterostigma location, pterostigma loading, elastic modulus and density. The results of this study can be used as a reference in future BMAV wing optimization design.

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