Computational Fluid Dynamics Study of NACA 0012 Airfoil Performance with OpenFOAM®

2021 ◽  
Vol 14 (4) ◽  
pp. 201
Author(s):  
Edwin Espinel ◽  
Jhan Piero Rojas ◽  
Eder Florez Solano
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Naca 0012

scholarly journals Lift Force of Airfoil (NACA 0012, NACA 4612, NACA 6612) With Variation of Angle of Attack and Camber: Computational Fluid Dynamics Study

2021 ◽  
Vol 4 (2) ◽  
pp. 80
Author(s):  
Mariza D. Ardany ◽  
Paken Pandiangan ◽  
Moh. Hasan
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Flow Rate ◽  
Lift Force ◽  
Angle Of Attack ◽  
Dynamics Simulation ◽  
Computational Fluid Dynamics Simulation ◽  
Internal Factors ◽  
Airfoil Flow ◽  
Naca 0012

Airfoil is a cross section from air plane wings can affect aerodynamic performance to lift force (FL). The lift force generated by airfoil has different values due to several external and internal factors, including angle of attack, flow rate and camber. To find the lift force of airfoils with different cambers and variations angle of attack and then flow rate can use computational fluid dynamics simulation. Computational fluid dynamics is simulation on a computer that can complete systems for fluid, heat transfer and other physical processes. This research using computational fluid dynamics simulation performed by SolidWorks, with NACA airfoil type which has different camber NACA 0012, NACA 4612 and NACA 6612. The angle of attack used in research was 0o, 4o, 8o, 12o, 16o and 20o. Flow rate used in research was 20m/s, 40 m/s, 60 m/s, 80 m/s and 100 m/s. From this research will be the bigger camber can produce a greater force lift. In addition, the greater airfoil flow rate can produce a greater force lift. This research also that the connection between force lift with coefficient lift (CL) is nonlinear quadratic form.

scholarly journals Comparison of Aerodynamic Characteristics of NACA 0012 and NACA 2412 Airfoil

2021 ◽  
Vol 9 (VII) ◽  
pp. 2037-2045
Author(s):  
S. M Mehady Hasan
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Steady State ◽  
Experimental Methods ◽  
Aerodynamic Characteristics ◽  
Steady State Flow ◽  
Pressure Contour ◽  
Computational Fluid Dynamics Cfd ◽  
Velocity Contour ◽  
Naca 0012

A comparison between NACA 0012 and NACA 2412 has been made by comparing the lift co- efficient, drag co-efficient, pressure contour and velocity contour at various angles of attack. The process has been done taking steady state flow around NACA-0012 and NACA-2412 airfoil using 1m chord length and a velocity of 88.65m/s. The main aim is to understand the aerodynamic characteristics of both the airfoils at different angles of attack and draw a conclusion on which performs better under the same conditions. Modelling and numerical analysis has been carried out by using commercially available CFD software, which is a convenient method of analysis since computational methods are more preferred to experimental methods due to low expenses involved. The numerical results demonstrated are compatible with those of the theory. This confirms the validity of using Computational Fluid Dynamics (CFD) as a reliable alternative to experimental procedures.

ANÁLISE NUMÉRICA DO ESCOAMENTO E DOS COEFICIENTES AERODINÂMICOS EM AEROFÓLIOS SEM E COM A UTILIZAÇÃO DE FLAPS PLAIN

2018 ◽  
Vol 12 (1) ◽  
pp. 45
Author(s):  
William Denner Pires Fonseca ◽  
Lourival Matos de Sousa Filho ◽  
Genilson Vieira Martins
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Navier Stokes ◽  
Ansys Fluent ◽  
Naca 0012

<p class="04CorpodoTexto">Este trabalho apresenta o estudo numérico do escoamento e das características aerodinâmicas em aerofólios simétrico e assimétrico sem e com flap. Um modelo bidimensional, permanente e viscoso é adotado no problema. As equações da conservação de massa (Continuidade) e da conservação de movimento (Navier-Stokes) são diferenciadas pelo método dos volumes finitos através do software CFD (<em>Computational Fluid Dynamics</em>) ANSYS/Fluent™. Inicialmente o código numérico é validado com a comparação dos resultados obtidos numa simulação para um aerofólio da série NACA 4 dígitos sem flap com os resultados apresentados na literatura. Em seguida buscou-se averiguar como se comporta os campos de pressão e velocidade, as linhas de corrente, os coeficientes de sustentação e arrasto para os aerofólios simétrico (NACA 0012) e assimétrico (EPLLER 423) sem e com flap. Por fim é verificado qual aerofólio é mais eficiente aerodinamicamente.</p>

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