Fluid dynamic analyses of unsteady thrust generation by dolphin fluke

Thermal performances of 3D SiP (system-in-package) with TSV (through silicon via) interposer/chip are investigated based on heat-transfer CFD (computational fluid dynamic) analyses. Emphases are placed on the determination of (1) the equivalent thermal conductivity of interposers/chips with various copper-filled, aluminum-filled, and polymer w/o filler filled TSV diameters, pitches, and aspect ratios, and (2) the junction temperature and thermal resistance of 3D SiP with various TSV parameters. Useful design charts and guidelines are provided for engineering practice convenient.

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Daniel K. Inouye Solar Telescope: computational fluid dynamic analyses and evaluation of the air knife model

10.1117/12.2231891 ◽

2016 ◽

Cited By ~ 1

Author(s):

Isaac McQuillen ◽

LeEllen Phelps ◽

Mark Warner ◽

Robert Hubbard

Keyword(s):

Computational Fluid Dynamic ◽

Fluid Dynamic ◽

Solar Telescope ◽

Dynamic Analyses ◽

Air Knife

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Numerical Analysis of Aerofoil Shape Propeller Boss Cap Fin (PBCF) to Improve Propeller Efficiency

International Journal of Innovative Technology and Exploring Engineering - Special Issue ◽

10.35940/ijitee.c8036.019320 ◽

2020 ◽

Vol 9 (3) ◽

pp. 231-238

Keyword(s):

Fossil Fuel ◽

Fluid Dynamic ◽

Environmental Issues ◽

Navier Stokes ◽

Pressure Side ◽

Flow Phenomenon ◽

Thrust Generation ◽

Propeller Performance ◽

High Thrust ◽

Marine Vehicle

Scarcity in fossil fuel and other environmental issues forced researchers to search ways to improve in the efficiency of the marine vehicle which is considered the most efficient and economic transport medium now a day. Energy saving device (ESD) is such an implementation to keep dominant impact in this aspect. This paper investigates the effect of aerofoil shape propeller boss cap fin (PBCF) as ESD computationally. Based on Reynolds- averaged Navier-Stokes (RANS) equations, numerical simulations have been performed to increase propeller efficiency with aerofoil shape propeller boss cap fin in computational fluid dynamic (CFD) approach. In this study, four separate aerofoil shape PBCF with different NACA profile (NACA4412, NACA0012, NACA1412, NACA2412) has been used to find a suitable profile for PBCF. Numerical results shows aerofoil shape PBCF with NACA4412 effectively improves propeller performance by improving the efficiency by approximately 3.52% than parent propeller. The pressure distribution elaborate PBCF (NACA4412) creates a high pressure difference between the pressure side and suction of the propeller as well as high thrust generation. Besides that velocity filed, swirl strength are also studied to get and understand the details of involved flow phenomenon.

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Computational Fluid Dynamic Analyses to Establish Design Process of Centrifugal Blood Pumps

Artificial Organs ◽

10.1046/j.1525-1594.1998.06169.x ◽

1998 ◽

Vol 22 (5) ◽

pp. 381-385 ◽

Cited By ~ 36

Author(s):

Yuki Miyazoe ◽

Toshio Sawairi ◽

Kazuyuki Ito ◽

Yoshiaki Konishi ◽

Takashi Yamane ◽

...

Keyword(s):

Design Process ◽

Computational Fluid Dynamic ◽

Fluid Dynamic ◽

Blood Pumps ◽

Dynamic Analyses

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Computational Analysis of a Truss Type Fuselage

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.225.183 ◽

2012 ◽

Vol 225 ◽

pp. 183-188

Author(s):

Ismail Abdelrahman Yousif ◽

Mohammed Abdelmageed M. Zein ◽

Mohammed Elhadi Ahmed Elsayed

Keyword(s):

Fluid Dynamic ◽

Small Region ◽

Landing Gear ◽

Principal Stresses ◽

Aerodynamic Loads ◽

Design Procedures ◽

Dynamic Analyses ◽

Rear Part ◽

Von Mises ◽

Von Mises Stresses

The strength of a welded truss type fuselage of a light aircraft – named SAFAT 01 – is considered in this paper. The aircraft is a monoplane with high strut-braced wings configuration with flaps. The fuselage is of welded tubular steel fabric-covered construction. According to its production contract; the aircraft is fully produced and assembled in Sudan whereas the documentation is limited to technical side only with no information available about design procedures and calculations. This makes it difficult to further modify or upgrade the aircraft. The fuselage geometry has been modeled using a CAD program. The main dimensions have been obtained using 2-D drawings and the missing dimensions and data due to lack of documents were extracted experimentally from a built aircraft. Aerodynamic loads were determined using computational fluid dynamic program for the horizontal tail. Static structural analysis was conducted by finite element method (FEM) using fastened connection property between the tubes. The results were observed in three main parts; rear part which supports the vertical and horizontal stabilizers and the rear landing gear; the mid part which provides cantilever reaction for the wing and supports front landing gear, and the front part on which the engine is mounted. The Von Mises stresses, displacements and principal stresses were observed in the three parts and found acceptable except for a small region near the attachment between wing and fuselage. However, further experimental validation is needed. Presently, experimental and dynamic analyses are being conducted and the results will be published later.

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