NACA AIR FOIL TEST AT DIFFERENT ATTACK ANGLES

                               NACA AIR FOIL TEST AT DIFFERENT ATTACK ANGLES

INTRO:

In this project we will test the air foil at different attack angles in the solid works saoftware by taking the data from the NACA sample file. in this analysis we will test the air foil at different attack angles and obtain the data of the force in different planes and we will see the velocity and the pressure effects on the surface of the air foil.

PROCEDURE FOR TESTING :

1. we will create the model by extracting the data from the file in the solid works software.
2. we will make the model to be closed by  drawing the line by connecting two end points at end of the air foil.
3. we convert the entire curve into the sketch by clicking on the convert entities.
4. Extrude up to certain length by clicking on the extrude button.
5. now setup external flow simmulation with the time dependent analysis of taking 5s of time with 1s interval.
6. give the velocity in x-direction as 600m/s
7. now define the computational domain by taking inlet as 5 times chaord lenght and outlet as 10-15 times of the chord length.
8. now setup the goals of drag and lift force in x,y direction and veloctiy define mesh and refine the local mesh.
9. run the simulation observe the cut plots at 0,2,4,6,8,10 attack angles and observe the data.

VELOCITY PROFILE AT ATTACK ANGLE 0° :

Velocity 

The air foil that is simulated at 0° attack angle and 600m/s velocty. The output parameters that have taken is total force acting in the x-direction and y-direction and the drag force that is produced in the x and y direction at the surface of the air-foil, the froce and the drag force produced in x - direction is same because the attack angle is 0°. we can see  that whenever working fluid (air) strikes the surface of the air foil ,the flow splits into the two directions and then gradually converges at the tail end.

VELOCITY PROFILE ATTACK ANGEL AT 2° 

The air foil that is simulated at 0° attack angle and 600m/s velocty. The output parameters that have taken is total force acting in the x-direction and y-direction and the drag force that is produced in the x and y direction at the surface of the air-foil, the maximum and the minimum drag force produced in x -direction and y-direction is 0.00224385 Nand 0.00385448 N .At the attack angle of 2° , whenever the air fluid strikes the air foil the splits into two profiles and resistance is offered by the upper fluid and lift produced by the lower profile so in this case the lift is more.

VELOCITY PROFILE ATTACK ANGEL AT 4° 

 The air foil that is simulated at 4° attack angle and 600m/s velocty. The output parameters that have taken is total force acting in the x-direction and y-direction and the drag force that is produced in the x and y direction at the surface of the air-foil, the maximum and the minimum drag force produced in x -direction and y-direction is 0.00265869 Nand 0.00776963 N.At the attack angle of 4° , whenever the air fluid strikes the air foil the splits into two profiles and resistance is offered by the upper fluid and lift produced by the lower profile so in this case the lift is more.

VELOCITY PROFILE ATTACK ANGEL AT 6° 

 The air foil that is simulated at 6° attack angle and 600m/s velocty. The output parameters that have taken is total force acting in the x-direction and y-direction and the drag force that is produced in the x and y direction at the surface of the air-foil, the maximum and the minimum drag force produced in x -direction and y-direction is 0.00337162 N and 0.00341372 N.At the attack angle of 6° , whenever the air fluid strikes the air foil the splits into two profiles and resistance is offered by the upper fluid and lift produced by the lower profile so in this case the lift is more.

VELOCITY PROFILE ATTACK ANGEL AT 8° 

 The air foil that is simulated at 8° attack angle and 600m/s velocty. The output parameters that have taken is total force acting in the x-direction and y-direction and the drag force that is produced in the x and y direction at the surface of the air-foil, the maximum and the minimum drag force produced in x -direction and y-direction is 0.00445949 N and 0.0156712 N.At the attack angle of 8° , whenever the air fluid strikes the air foil the splits into two profiles and resistance is offered by the upper fluid and lift produced by the lower profile so in this case the lift is more.

 VELOCITY PROFILE ATTACK ANGEL AT 10° 

The air foil that is simulated at 10° attack angle and 600m/s velocty. The output parameters that have taken is total force acting in the x-direction and y-direction and the drag force that is produced in the x and y direction at the surface of the air-foil, the maximum and the minimum drag force produced in x -direction and y-direction is 0.00573288 Nnd 0.0197043 N.At the attack angle of 10° , whenever the air fluid strikes the air foil the splits into two profiles and resistance is offered by the upper fluid and lift produced by the lower profile so in this case the lift is more.

OBSERVATION:

From the data we can summarise that the increasing of the downward angle increases the lift of the plane and decreases the drag force . To increase the drag force we need to incerease upward angel of the airfoil.

NOTE : ALL THE VALUES OF THE DATA WAS TAKEN AT THE TIME OF THE SIMULATION

LINK FOR DAT FILE:https://drive.google.com/open?id=1q5NZgFmV6Kw0LRoQgyOshFGiFptjI-3i