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

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.

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

10.1063/1.5115903 ◽

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

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Computational Study of the Aerodynamic Performance of Subsonic Scarf Inlets

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit ◽

10.2514/6.2004-3406 ◽

2004 ◽

Cited By ~ 1

Author(s):

John Abbott

Keyword(s):

Computational Study ◽

Aerodynamic Performance

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

The Open Aerospace Engineering Journal ◽

10.2174/1874146001205010011 ◽

2012 ◽

Vol 5 (1) ◽

pp. 11-21 ◽

Cited By ~ 5

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.

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AERODYNAMIC PERFORMANCE AND FLOW STRUCTURE OVER A THIN AIRFOIL UNDER SMOOTH AND TURBULENT CONDITIONS AT LOW REYNOLDS NUMBERS

Journal of Flow Visualization and Image Processing ◽

10.1615/jflowvisimageproc.2012003945 ◽

2011 ◽

Vol 18 (3) ◽

pp. 253-274 ◽

Cited By ~ 1

Author(s):

Sridhar Ravi ◽

P. Petersen ◽

S. Watkins ◽

M. Marino ◽

J. Watmuff

Keyword(s):

Flow Structure ◽

Reynolds Numbers ◽

Aerodynamic Performance ◽

Low Reynolds Numbers ◽

Thin Airfoil ◽

Low Reynolds

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Computational Study on Pressure Side Film Cooling and Flow Structure

ASME 2013 Gas Turbine India Conference ◽

10.1115/gtindia2013-3696 ◽

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.

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