Challenge

Flow over an airfoil

SShahbaaz Khan Deoda22 Jun 2020

REPORT ON NACA AIRFOIL ANALYSIS FOR DIFFERENT ANGLE OF ATTACK

Created by Shahbaaz Khan Deoda

On June 2020

AIM: -To perform a analysis on NACA 0017 airfoil for different angle a of attack and evaluate the plot for drag force and lift force.

OBJECTIVE: - 1. Modal the NACA 0017 airfoil.

evaluate the plot for drag and lift force for angle of attack of 0, 2, 4, 6, 8 and 10 degree.

PHYSICS: -

angle of attack: -In aerodynamics, angle of attack specifies the angle between the chord line of the wing of a fixed wing aircraft and the vector representing the relative motion between the aircraft and the atmosphere. Since a wing can have twist, a chord line of the whole wing may not be definable, so an alternate reference line is simply defined. Often, the chord line of the Feet of the wing is chosen as the reference line. Another choice is to use a horizontal line on the fuselage as the reference line (and also as the longitudinal axis). Some authors do not use an arbitrary chord line but use the zero-lift axis where, by definition, zero angle of attack corresponds to zero coefficient of it.

Governing equation: -

Drag force: -

2. Lift force: -

CONDITIONS:

The problem consists of flow around an airfoil at various angles of attack (0, 2, 4, 6, 8, 10 degrees).

External Flow

Fluid: AIR

Time Dependent: - Total Analysis Time - 5 s

Output Time Step - 1 s

Density = 1.225 kg/m^3

Inlet Velocity = 600 m/s

PROCEDURE:

An airfoil is created by using convert entities then line command.
For the different angle of attacks rotate entities is used.
The airfoil is extruded to 0.195 meter. Now save the file.
The flow simulation is created using the wizard menu.
The analysis type is selected as external. Time-dependent is selected.
Total analysis time is selected as 5 sec and output time is 1sec.
The fluid is selected as air and velocity parameter over X-direction is selected as 600m/s and then click finish.
Now a computational domain is created by using the 2D option.
The computational domain is expanded along both y-directions and x-direction in such a way that the length after the wake region should be 5 times the length ahead of wake region.
The Global mesh is defined and the local mesh is defined by selecting the surface. It is refined up to a level of 3.
The goals option is selected then force x and force y selected after selecting the surface.
Run the simulation.
Now a cut plot is made along x-direction and velocity over the airfoil is selected.
Colour refining is given 100.
A goal plot is plotted between drag force along the x-direction and lift along the y-axis.
The above procedure is followed for different attack angles and the following results are used to plot the necessary graphs.

Results

Results are computed and studied on different angle of attacks.

let's run one by one on the different angle of attacks.

Here,

Integrated force along the x-axis is Drag force(SG Force x1).
Integrated force along the y-axis is Lift force(SG Force y2).

Case 1: Angle of attack 0 degree