report aerodynamics begginer

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2015

Jose Pardellas Bello & Marcos Benedí

European University of Madrid UEM

Aerospace Engineering in Aircrafts

Aerodynamic Airfoil – Wing Project


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Aerodynamics Politechnnical School

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INDEX

Introduction And Data

2D Analysis. Conclussions

3D Analysis. Conclussions

Comparisson 2D & 3D.

Final Conclussions


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Introduction to the Project And Relevant Data to be used:

The main objective of the project is to obtain acknowledgments on how an airfoil and a wing

behaves in experimental analysis process.

We have to take into consideration that the airfoil we have used is an airfoil that may not fit

real flight conditions; and that flight conditions that we have assume for each airfoil may not

be the correct ones to obtain real values for our profile; we assume a lot of flight conditions as

flight velocity; height at steady state; density of the fluid in where the airfoil is analyzed;

treated the fluid as air; and all assumptions it concerns relates to air flow model.

We have to know that the Root Chord measurements are 20 cm. and the span assumed to be

analyzed in 3D are 0,5m.


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ANALYSIS

We have to analyze an airfoil profile (2D) and an airfoil wing (3D).

ANALYSIS WITH XFLR 5 (2D)

1st we have to export our airfoil which we have created with EXCEL and a notepad page; taking

the measured points for our first airfoil profile; but after iterate our measured points with an

N-10 ideal profile with XFLR5; we obtain the airfoil profile which we going to operate during

the analysis (2D & 3D)

Airfoil Before Iteration; Green = N-10 & Red = Approach Airfoil Measures

Airfoil After Iteration & Airfoil taken for Ansys Analysis in 2D


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After interpolations, we obtain the next graph values:

Cl /Alpha Graph; we can see at 0 angle of attack we obtain a value near to 0,4 lift coefficient;

we have the Zero lift angle of attack near to -3.5

At 0 angle of attack, we obtain a Lift to Drag Coefficient ratio of 24


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3D ANALYSIS

To make the 3D analysis we will start setting up the Xflow menu; and import the NACA

geometry saved in .igs format

We will set the wind tunnel and after interpolate with k-epsilon equations solutions &

introduce the velocity by components (from 10 to -10 degrees; taking 20 & -20 as extreme

values); taking 50 as Speed Module


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Setting XFLOW for 3D analysis

We start setting velocity as 50 m/s and the wind tunnel dimensions (2,2,2)

In orientation field, we have to set the angle of attack we want to analyze.

We set the simulation time & the scale which XFLOW will used as a mesh; we have to set the

frames frequency as well.


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Change the surface info part & the field too to obtain (Vorticity, Static Pressure, Cp

Distribution, and Velocity by Components) for each degree we have analyzed; to obtain the

graphs we will see later.


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0 Degree Angle of Attack

Cp Distribution

Static Pressure


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Vorticity

Velocity in X-Component


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Velocity in Y-Component


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2 Degrees Angle of Attack

Cp Distribution

Static Pressure


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Vorticity



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Cp Distribution

Static Pressure


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Cp Distribution

Static Pressure


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Vorticity



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Cp Distribution

Static Pressure


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Vorticity



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8 degrees Angle of Attack

Cp distribution

Static Pressure


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Vorticity



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Cp Distribution


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Static Pressure


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Vorticity


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Cp Distribution

Static Pressure


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Vorticity



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-2 Degrees Angle of Attack

Cp Distribution

Static Pressure


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Vorticity



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Cp Distribution

Static Pressure


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Vorticity



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Cp Distribution

Static Pressure


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Vorticity



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Cp Distribution

Static Pressure


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Vorticity



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Cp Distribution

Static Pressure


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Vorticity



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Cp Distribution

Static Pressure


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Vorticity



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Cp Distribution

Static pressure


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Vorticity



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At the same time we obtain those previous graphs with contours and surfaces distributions;

we obtain de Lift, Drag & Moment in Z-Component Coefficients for each angle of attack

previously analyzed.


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We use those values to create some plotted graphs to observe when the wing could be

consider stable.


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FINAL CONCLUSSION GRAPHS


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As we can see in the 2D graphs get with XFLR5 and compared with those ones we have obtain

or the 3D analysis with XFLOW, we can conclude that the stable zone for the wing that we

have study in our project is between the -5 to 0 degrees angle of attack region. Out of these

region, the wing can behaves in very rare ways; giving us a lot of lift or a lot of drag for 3

degrees variation.

Our wing does not behaves as a symmetric airfoil profile could behaves; even we have taken

the N-10 ideal airfoil design; but the interpolation with our approach measurements, change

completely the results of the analysis.

We can conclude that for the aerodynamic analysis of a wing we cannot take measurements

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