scholarly journals Computational study of aerodynamic performance and flow structure around NACA 23012 wing

2021 ◽  
Vol 7 (2) ◽  
pp. 89
Author(s):  
James Dent ◽  
Joshua Robson ◽  
Alessio Basso ◽  
Alexander Ellin ◽  
Atma Prakash ◽  
...  
Keyword(s):  
Flow Structure ◽  
Computational Study ◽  
Aerodynamic Performance

scholarly journals Computational study of aerodynamic performance and flow structure around NACA 23012 wing

2021 ◽  
Vol 7 (2) ◽  
pp. 89
Author(s):  
Atma Prakash ◽  
Alexander Ellin ◽  
F.A. Hamad ◽  
Alessio Basso ◽  
Joshua Robson ◽  
...  
Keyword(s):  
Flow Structure ◽  
Computational Study ◽  
Aerodynamic Performance

A Computational Study on Airfoils at a Low Reynolds Number

2000 ◽  
Author(s):  
Ajit Pal Singh ◽  
S. H. Winoto ◽  
D. A. Shah ◽  
K. G. Lim ◽  
Robert E. K. Goh
Keyword(s):  
Reynolds Number ◽  
Computational Analysis ◽  
Computational Study ◽  
Low Reynolds Number ◽  
Micro Air Vehicles ◽  
Reynolds Numbers ◽  
Aerodynamic Performance ◽  
Low Reynolds Numbers ◽  
Study Results ◽  
Low Reynolds

Abstract Performance characteristics of some low Reynolds number airfoils for the use in micro air vehicles (MAVs) are computationally studied using XFOIL at a Reynolds number of 80,000. XFOIL, which is based on linear-vorticity stream function panel method coupled with a viscous integral formulation, is used for the analysis. In the first part of the study, results obtained from the XFOIL have been compared with available experimental data at low Reynolds numbers. XFOIL is then used to study relative aerodynamic performance of nine different airfoils. The computational analysis has shown that the S1223 airfoil has a relatively better performance than other airfoils considered for the analysis.

Improvement in aerodynamic performance of NACA0021 airfoil using moving surface boundary layer: A computational study

2019 ◽  
Author(s):  
Md. Abdus Salam ◽  
Vikram Deshpande ◽  
Shoyon Panday ◽  
Nafiz Ahmed Khan ◽  
M. A. Taher Ali
Keyword(s):  
Boundary Layer ◽  
Computational Study ◽  
Aerodynamic Performance ◽  
Surface Boundary ◽  
Moving Surface ◽  
Surface Boundary Layer

scholarly journals A Computational Study on the Aerodynamic Influence of a Propeller on an MAV by Unstructured Overset Grid Technique and Low Mach Number Preconditioning

2012 ◽  
Vol 5 (1) ◽  
pp. 11-21 ◽  
Author(s):  
S. Deng ◽  
B. W. van Oudheusden ◽  
T. Xiao ◽  
H. Bijl
Keyword(s):  
Computational Study ◽  
Aerodynamic Performance ◽  
Moving Boundaries ◽  
Simulation Tool ◽  
Overset Grid ◽  
Low Mach Number ◽  
Speed Flow ◽  
Grid Approach ◽  
Preconditioning Method ◽  
Grid Technique

The influence of a propeller on the aerodynamic performance of an MAV is investigated using an unstructured overset grid technique. The flow regime of a fixed-wing MAV powered by a propeller contains both incompressible regions due to the low flight speed, as well as compressible flow areas near the propeller-tip region. In order to simulate all speed flow efficiently, a dual-time preconditioning method is employed in the present study. The methodology in this paper is verified as providing a reliable numerical simulation tool for all flow regimes, in the additional presence of moving boundaries, which is treated with an overset grid approach.

Computational Study on Pressure Side Film Cooling and Flow Structure

2013 ◽  
Author(s):  
Radheesh Dhanasegaran ◽  
Girish Venkatachalapathy ◽  
Nagarajan Gnanasekaran
Keyword(s):  
Flow Structure ◽  
Film Cooling ◽  
Computational Study ◽  
Pressure Side ◽  
Cooling Performance ◽  
Pressure Surface ◽  
Blowing Ratio ◽  
Commercial Code ◽  
Cylindrical Holes ◽  
Specific Geometry

A computational investigation is carried out to understand the film cooling performance and flow phenomenon on a pressure side of gas turbine airfoil. A specific geometry with multiple rows of cylindrical holes is considered on the pressure surface and opposite to which a flat surface is kept so as to avoid effect of imposed flow conditions. Meshing of the present model is done by using GAMBIT. Computations are carried out with K-epsilon Realizable model available in the commercial code FLUENT. The film cooling performance is discussed with flow structure followed by the effectiveness distribution on the pressure surface. The blowing ratio is varied from 0.4–2.4 and it is found that, at very low blowing ratio cases in the initial part of the pressure surface higher effectiveness values are observed but at higher blowing ratio these values become very low whereas close to the trailing edge side the effectiveness distribution is just the reverse. It was found that the optimum blowing ratio was close to unity where better flow and temperature distribution were observed.

scholarly journals A Computational Study on the Flow Structure around a Yawed Circular Cylinder

2003 ◽  
Vol 28 (1) ◽  
pp. 94_107-94_116
Author(s):  
Yutaka HARA ◽  
Hiroshi HIGUCHI ◽  
Tetuya KAWAMURA ◽  
Tsutomu HAYASHI
Keyword(s):  
Circular Cylinder ◽  
Flow Structure ◽  
Computational Study
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