CFD Analysis of an Aerofoil

Patel, Karna S.; Patel, Saumil B.; Patel, Utsav; Ahuja, Ankit P.

doi:10.17950/ijer/v3s3/305

Cited by 41 publications

(23 citation statements)

References 1 publication

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“…For the airfoil, the relevant surface area, which is related to the drag coefficient types, is a plane form area [3]. T. Benson [4] mentioned from NASA, the lift coefficient is usually determined experimentally, meanwhile it is a number which could describe all the complex dependencies of shape, inclination and some flow conditions on aircraft lift.…”

Section: Lift and Dragmentioning

confidence: 99%

“…The angle of attack, as it is showed in Figure 3, is the angle between the relative wind and the chord. As the leading edge which is front point of the airfoil turns up, angle of attack increases and connected to the increase of the lift force and drag force [3]. Investigations from former work from Sahin et al [6] analysed the impact of stalling angle on lift and drag coefficient.…”

Section: Reynolds Numbermentioning

confidence: 99%

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Investigation of Flow over the Airfoil NACA 0010-35 with Various Angle of Attack

Xiao

Chen

2018

MATEC Web Conf.

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Abstract. This report is using the finite element analysis method to investigate the performance of an airfoil (NACA 0100-35), which uses 2D computational fluid dynamics simulations based on ANSYS to find the lift and drag coefficients under different conditions. The boundary conditions are defined as follows: The density is 1kg/ , gauge pressure is 0, and airflow velocity is 50m/s. Also the Reynolds number is considered during the simulation. As a result, the simulation shows the stalling points and efficiencies of the airfoil under different angles of attack. The simulation also plots the contours and stream lines in these conditions.

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Section: Lift and Dragmentioning

confidence: 99%

Section: Reynolds Numbermentioning

confidence: 99%

Investigation of Flow over the Airfoil NACA 0010-35 with Various Angle of Attack

Xiao

Chen

2018

MATEC Web Conf.

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“…The flow condition determines the flow characteristics and performance of the airfoil. As the airfoil has been placed within a freestream flow, the aerodynamics forces have been produced [1]. The airfoil that is subjected to compressible flow has a higher lift compared to incompressible flow due to higher freestream velocity experienced by the airfoil.…”

Section: Introductionmentioning

confidence: 99%

Research on Flows for NACA 2412 Airfoil using Computational Fluid Dynamics Method

Kharulaman¹,

Aabid²,

Mehaboobali³

et al. 2019

IJEAT

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The comparison between incompressible and compressible flow for aerodynamic coefficients and flow characteristics has been made for NACA 2412 airfoil. The FEM is used to obtain results. The fluid domain of 10C has been constructed to initialize the boundary conditions of incompressible and compressible flow conditions. The structured mesh has been applied in order to achieve accurate results. The Spallart-Allmaras turbulence model has been used to solve both incompressible and compressible flow conditions. The method validation that has been conducted at incompressible flow has shown close agreement between numerical and experimental lift coefficient. From velocity magnitude and static pressure, contours, the compressible flow has the highest-pressure distribution compared to incompressible flow. Therefore, it has been proven that the coefficient of force at ninety degrees to the direction of the flow direction of the airfoil subjected to a variable density flow was much higher compared to incompressible flow.

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“…Comparatively air flows in straighter line below the wing. Thus speed and air pressure remains the same for the shape [1]. Angle of attack, leading edge, trailing edge, span length, chord length, lift force, drag force and thickness all of them have to be clearly defined and be calculated from geometry of aerofoil [2].…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Investigation of Aerodynamics Characteristics of NACA 0015 Aerofoil

Rubel

Uddin

Islam

et al. 2017

International Journal of Engineering Technologies IJET

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Abstract-An aerofoil is a streamline body. Symmetric aerofoil (NACA 0015) is used in many applications such as in aircraft submarine fins, rotary and some fixed wings. The ultimate objective of an aerofoil is to obtain the lift necessary to keep an airplane in the air. But construction of the blade with proper angle of attack and implementation has significant effect on lift force. Insufficient lift force might cause fail of airplane flying, especially at high speed. Modern technologists use different simulation techniques to avoid costly model testing. But simulation is based on some assumption. Thus practically results are not fully authentic and have a deviation. In this work numerical and experimental investigation of NACA 0015 is studied at different angle of attack (degree) at different velocity of air by determining the forces at every two degrees from 0 0 to 18 0 . The experiment is conveyed in a low speed wind tunnel. The numerical analysis is conducted using ANSYS (combined with CFD and FLUENT FLOW). The use of the CFD technology greatly reduces the overall investment and efforts for aerofoil design. CFD method contributes to visualize the flow pattern inside aerofoil and takes less time and comparatively faster than experiment. After completing the experimental, numerical data is compared. Therefore, the objective of this paper is to find the deviation and validation of aerodynamics characteristics of NACA 0015 aerofoil for experimental and numerical method.

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CFD Analysis of an Aerofoil

Cited by 41 publications

References 1 publication

Investigation of Flow over the Airfoil NACA 0010-35 with Various Angle of Attack

Investigation of Flow over the Airfoil NACA 0010-35 with Various Angle of Attack

Research on Flows for NACA 2412 Airfoil using Computational Fluid Dynamics Method

Numerical and Experimental Investigation of Aerodynamics Characteristics of NACA 0015 Aerofoil

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