scholarly journals Numerical Study of Wind-Tunnel Wall Effects on Lift and Drag Characteristics of NACA 0012 Airfoil

CFD letters ◽  
2020 ◽  
Vol 12 (11) ◽  
pp. 72-82
Author(s):  
Mostafa Abobaker ◽  
Sogair Addeep ◽  
Abdulhafid M. Elfaghi
Keyword(s):  
Wind Tunnel ◽  
Numerical Study ◽  
Published Data ◽  
Computational Domain ◽  
Tunnel Wall ◽  
Ansys Fluent ◽  
Slope Correction ◽  
Lift Curve ◽  
Lift And Drag ◽  
Naca 0012

Possible interference effects of the wind tunnel walls play an important role especially for measurements in closed-wall test sections. In this study, a numerical analysis of two-dimensional subsonic flow over a NACA 0012 airfoil at different computational domain heights, angles of attack from 0o to 10o, and operating Reynolds number of 6×106 is presented. The work highlights the role of computational fluid dynamics (CFD) in the investigation of wind tunnel wall effect on lift curve slope correction factor (Ka). The flow solution is obtained using Ansys Fluent software by solving the steady-state continuity and momentum governing equations combined with turbulence model k-v shear stress transport (SST-K?). The numerical results are validated by comparing with the available experimental measurements. Calculations show that the lift curve slope correction results are very close to the published data.

scholarly journals An Experimental Analysis on the Effects of Stagger on the Aerodynamic Forces of Tandem Wings

AVIA ◽  
2021 ◽  
Vol 2 (2) ◽  
Author(s):  
Y Parlindungan ◽  
S Tobing
Keyword(s):  
Experimental Analysis ◽  
Numerical Study ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Aerodynamic Performance ◽  
Open Loop ◽  
Aerodynamic Forces ◽  
Subsonic Wind Tunnel ◽  
Lift And Drag ◽  
Naca 0012

This study is inspired by the flapping motion of natural flyers: insects. Many insects have two pairs of wings referred as tandem wings. Literature review indicates that the effects of tandem wing are influenced by parameters such as stagger (the stream-wise distance between the aerodynamic center of the front and the rear airfoil), angle-of-attack and flow velocity. As a first stage, this study focuses on the effects of stagger (St) on the aerodynamic performance of tandem wings. A recent numerical study of stagger on tandem airfoils in turbulent flow (Re = 6000000) concluded that a larger stagger resulted in a decrease in lift force, and an increase in drag force. However, for laminar flow (Re = 2000), increasing the stagger was not found to be detrimental for aerodynamic performance. Another work also revealed that the maximum lift coefficient for a tandem configuration decreased with increasing stagger. The focus of this study is to perform an experimental analysis of tandem two-dimensional (2D) NACA 0012 airfoils. The two airfoils are set at the same angle-of-attack of 0° to 15° with 5° interval and three variations of stagger: 1c, 1.5c and 2c. The experiments are conducted using an open-loop-subsonic wind tunnel at a Reynolds number of 170000. The effects of St on the aerodynamic forces (lift and drag) are analyzed

scholarly journals A Research on Wind Tunnel on Drag Reduction in Aircraft Wing by Inducing Surface Roughness

2019 ◽  
Vol 8 (2S3) ◽  
pp. 25-28
Keyword(s):  
Surface Roughness ◽  
Wind Tunnel ◽  
Viscous Drag ◽  
Friction Drag ◽  
Aircraft Wing ◽  
Aerodynamic Efficiency ◽  
Stall Angle ◽  
Lift And Drag ◽  
Naca 0012 ◽  
Inducing Surface

Drag is a major issue that aircraft industries are facing today. Innumerable investigations are in progress which mainly focus on the methods to reduce drag. Improving the aerodynamic efficiency of the vehicle can resolve this drawback to a great extent. The aerodynamic efficiency is explained in L/D ratio, decreasing the drag component will increase the aerodynamic efficiency. In this research a methodology to reduce the drag by creating roughness over wing surface has been adopted. By adopting this surface roughness method, the transition of the air flow from the laminar to the turbulent region will result in less drag. This research is being carried out based on the above said theory. The outcome of this method can delay the flow separation in a wing which helps in increasing the lift. The roughness has reduced the coefficient of skin friction drag or viscous drag and increased the coefficient of lift along with the stall angle of attack. NACA 0012 airfoil was selected for this study. Aluminum wing models are fabricated with and without surface roughness and same has been tested in Wind Tunnel. The results are discussed in terms of Lift and Drag

Aerodynamic Degradation of Iced Airfoils: Experiments and CFD Simulations

2009 ◽  
Author(s):  
Z. Chara ◽  
V. Horak ◽  
D. Rozehnal
Keyword(s):  
Wind Tunnel ◽  
Pressure Distribution ◽  
Cfd Simulation ◽  
Panel Method ◽  
Ice Accretion ◽  
Cfd Simulations ◽  
Ansys Cfx ◽  
Lift And Drag ◽  
Naca 0012 ◽  
Ice Shapes

The phenomenon of in-flight icing may affect all types of aircraft. Presence of ice on wings can lead to a number of aerodynamic degradation problems. Thus, it is important to understand the different ice shapes that can form on the wings and how they affect aerodynamics. When compared to wings without ice, wings with ice indicate decreased maximum lift, increased drag, changes in pressure distribution, stall occurring at much lower angles of attack, increased stall speed, and reduced controllability. The in-house ice accretion prediction code R-ICE using 2-D panel method was developed. The CFD simulation with the software ANSYS CFX 11.0 was used to simulate flow around iced airfoils NACA 0012. These airfoils were experimentally investigated in a wind tunnel. The paper presents a comparison of lift and drag coefficients experimentally observed and numerically simulated.

scholarly journals Mesh Properties for RANS Simulations of Airfoil-Shaped Profiles: A Case Study of Rudder Hydrodynamics

2021 ◽  
Vol 9 (10) ◽  
pp. 1062
Author(s):  
Suli Lu ◽  
Jialun Liu ◽  
Robert Hekkenberg
Keyword(s):  
Near Field ◽  
Reynolds Numbers ◽  
Far Field ◽  
Computational Domain ◽  
Ansys Fluent ◽  
Marine Propellers ◽  
Computational Fluid Dynamics Cfd ◽  
Naca 0012 ◽  
Mesh Properties

A good mesh is a prerequisite for achieving reliable results from Computational Fluid Dynamics (CFD) calculations. Mesh properties include mesh types, computational domain sizes, and node distributions. However, in literature, we found no clear consensus about what these properties should be. In this article, we performed a case study on ship rudders to determine what the suitable mesh properties are for airfoil-shaped profiles. A classic NACA 0012 profile is chosen as an example, and commercial packages ANSYS ICEM are applied for meshing with an ANSYS Fluent solver. With a strategy in consideration of relationships among different mesh properties, a comprehensive parametric investigation is conducted to study the impacts of these properties on the accuracy of rudder hydrodynamic coefficients obtained by CFD methods. The step-by-step study outputs recommended Reynolds numbers, domain sizes, and near- and far-field node distributions for mesh types with distinct topology structures, i.e., C-mesh, O-mesh, H-mesh, and Hybrid-mesh. Specifically, the study shows that a critical Reynolds number is needed for the perspective of efficiency, while a domain extending 60 times of the chord length enables the boundary effects to be negligible. As for node distributions, the near-field nodes should be treated carefully, compared with those in the far-field. After that, corresponding mesh properties for different calculation objectives are illustrated in detail based on the characteristics of mesh types mentioned above. With the proposed strategy for mesh refinements, impacts of different mesh properties on rudder hydrodynamics are clarified and recommended settings are applicable for other airfoil-shaped profiles such as wind turbines and marine propellers.

scholarly journals Numerical Examination on the Effect of Internal Fluid Presssure on the Hydrodynamic Response of a Marine Riser

2019 ◽  
Vol 8 (11S) ◽  
pp. 1310-1315
Keyword(s):  
Fatigue Damage ◽  
Numerical Study ◽  
Ansys Fluent ◽  
Drag Forces ◽  
Hydrodynamic Loading ◽  
Sea Bed ◽  
Exploration And Production ◽  
Helical Strakes ◽  
Initial Work ◽  
Lift And Drag

Marine risers are long slender structures which links the floating vessel on the sea surface and its manifold on the sea bottom. It acts as a transportation means for the hydrocarbon resources underneath the sea bed. A riser mainly undergoes hydrodynamic loading which leads to Vortex induced vibrations (VIV) or Flow induced vibrations. These are motions induced on bodies interacting with an external fluid flow producing periodic irregularities on the flow which leads to fatigue damage of offshore oil exploration and production risers. Therefore, suppressing of VIV by providing helical strakes, fairings etc. is necessary in order to reduce the fatigue damage of risers due to hydrodynamic loading. The present paper deals with the numerical study on the response of a marine riserdue to the effect of internalfluid pressure. The initial work is carried out in ANSYS ICEM CFD software. The CFD solution after analysis is obtained from ANSYS FLUENT. The hydrodynamic effects like lift and drag forces along with motion responses is obtained.

scholarly journals Hydrodynamic Characterization of thePolyodon spathulaRostrum Using CFD

2013 ◽  
Vol 2013 ◽  
pp. 1-8 ◽  
Author(s):  
Jeffrey B. Allen ◽  
Guillermo Riveros
Keyword(s):  
Numerical Study ◽  
Filter Feeding ◽  
Unique Shape ◽  
Lift And Drag ◽  
Naca 0012

Among the various functions of the paddlefish rostrum, it is also believed to serve as a stabilizer to counteract the downward force that would otherwise occur during the process of filter feeding. From its unique shape, it is hypothesized that the paddlefish rostrum serves to generate a substantial amount of lift that naturally occurs as the rostrum is elevated at the same time the fish opens its mouth. The present, numerical study is an attempt to quantify the amount of lift (and drag) that is generated by the rostrum of a juvenile paddlefish. Additionally, this data is compared with other hydrofoils. The results suggest that the paddlefish rostrum does indeed produce substantial lift at certain angles of attack. In fact, the results indicate that the amount of lift is comparable to that produced by a symmetric foil (NACA 0012).

Design Optimization and Analysis of NACA 0012 Airfoil Using Computational Fluid Dynamics and Genetic Algorithm

2014 ◽  
Vol 664 ◽  
pp. 111-116 ◽  
Author(s):  
R.K. Ganesh Ram ◽  
Yashaan Nari Cooper ◽  
Vishank Bhatia ◽  
R. Karthikeyan ◽  
C. Periasamy
Keyword(s):  
Reynolds Numbers ◽  
Ansys Fluent ◽  
Airfoil Optimization ◽  
Drag Forces ◽  
Fluent Software ◽  
Numerical Computing ◽  
Cfd Method ◽  
Lift And Drag ◽  
Naca 0012 ◽  
Mathematical Relations

CFD method is inexpensive method of analysis of flow over aerodynamic structure. It incorporates mathematical relations and algorithms to analyze and solve the problems regarding fluid flow. CFD analysis of an airfoil produces results such as lift and drag forces which determines the ability of an airfoil. Optimization of an airfoil involves improving the design of the airfoil in order to manipulate the lift and drag coefficients according to the requirements. It is a very common method used in all fields of engineering. MATLAB is a numerical computing environment which supports interface with other software. XFoil is airfoil analysis software which calculates the lift and drag characteristics for different Reynolds numbers, Mach numbers and angles of attack. MALAB is interfaced with XFoil and the optimization of NACA 0012 airfoil is done and the results are analyzed. The performance of optimized air foil is analyzed using ANSYS FLUENT software.

scholarly journals Numerical study of new techniques drag reduction: application to aerodynamic devices

2021 ◽  
Vol 12 ◽  
pp. 16
Author(s):  
Amine Agriss ◽  
Mohamed Agouzoul ◽  
Abdeslem Ettaouil ◽  
Abdessamad Mehdari
Keyword(s):  
Laminar Flow ◽  
Drag Reduction ◽  
Numerical Study ◽  
The Body ◽  
Test Cases ◽  
Ansys Fluent ◽  
New Techniques ◽  
Reduction Techniques ◽  
First Case ◽  
Naca 0012

In the present study, new drag reduction techniques applied to aerodynamic structures have been developed. The test cases have been numerically performed using three simplified models. Simulations have been performed by using the CFD software Ansys fluent. The first case deals with a laminar flow over a flat plate. Drag reduction is obtained by corrugating the shape of the plate. The second case treats a laminar flow over a NACA 0012 airfoil. By the addition of a device fixed on the flow separation point, the drag could be reduced. The last case concerns a turbulent flow over the Ahmed body. Drag reduction is obtained by the perforation of a conduit leading a part of the flow from the front to be injected at the rear of the body.

scholarly journals Numerical Study of the Reliability of Wind-Tunnel Wall Corrections for Wingtip Flow

2017 ◽  
Vol 54 (1) ◽  
pp. 354-358 ◽  
Author(s):  
Antoine Joulain ◽  
Damien Desvigne ◽  
David Alfano ◽  
Thomas Leweke
Keyword(s):  
Wind Tunnel ◽  
Numerical Study ◽  
Tunnel Wall

scholarly journals Numerical Study of the Air Flow over a NACA 0015 Wind Turbine Airfoil

2018 ◽  
Author(s):  
Houari Ameur ◽  
Karima Boukhadia
Keyword(s):  
Pressure Distribution ◽  
Numerical Study ◽  
Computer Code ◽  
Computational Domain ◽  
Computer Tool ◽  
Wind Turbine Airfoil ◽  
Lift And Drag ◽  
Volume Method ◽  
Icem Cfd ◽  
Naca 0015

A numerical study of the flow over a NACA aerofoil is presented in this paper. The numerical simulations are achieved with the computer code CFX and the computational domain is created by the computer tool ANSYS ICEM CFD. The CFX code is based on the finite volume method to solve the equations of mass, momentum and energy. The purpose of this paper is to determine the pressure distribution, flow patterns and the forces acting on the airfoil. Effects of the attack angle and Reynolds number on the velocity and pressure distribution, on the lift and drag coefficients are also explored.

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