Project

STUDY OF NACA AIR FOIL BY CHANGING THE ANGLE OF ATTACK

CCitharanjith Muruganantham21 Oct 2018

for 0 degree angle of attack:https://drive.google.com/file/d/1dL9qlGpduY3C0Hp0MRnhpnM9IcAuD6kM/view?usp=sharing

for 2 degree angle of attack:https://drive.google.com/file/d/1vDnLdnx4L7kmPPbPx4X5lHBI-z9ICcC0/view?usp=sharing

for 4 degree angle of attack:https://drive.google.com/file/d/1xG6caebJzrBgvL6-WJJvZ2OLJgxhl9Xc/view?usp=sharing

for 6 degree angle of attack:https://drive.google.com/file/d/1nR5tCtv_u0KFAgeqln361H9I1HFcAJ3O/view?usp=sharing

for 8 degree angle of attack:https://drive.google.com/file/d/1WgeDIwiFueuvOEiCZ5X3iaPUJTDA5aPf/view?usp=sharing

for 10 degree angle of attack:https://drive.google.com/file/d/1hZUqIzPIo-SI6HoQne4S1IWtr9m2sqGn/view?usp=sharing

for 0 degree angle of attack:https://drive.google.com/file/d/1dL9qlGpduY3C0Hp0MRnhpnM9IcAuD6kM/view?usp=sharing

for 2 degree angle of attack:https://drive.google.com/file/d/1vDnLdnx4L7kmPPbPx4X5lHBI-z9ICcC0/view?usp=sharing

for 4 degree angle of attack:https://drive.google.com/file/d/1xG6caebJzrBgvL6-WJJvZ2OLJgxhl9Xc/view?usp=sharing

for 6 degree angle of attack:https://drive.google.com/file/d/1nR5tCtv_u0KFAgeqln361H9I1HFcAJ3O/view?usp=sharing

for 8 degree angle of attack:https://drive.google.com/file/d/1WgeDIwiFueuvOEiCZ5X3iaPUJTDA5aPf/view?usp=sharing

for 10 degree angle of attack:https://drive.google.com/file/d/1hZUqIzPIo-SI6HoQne4S1IWtr9m2sqGn/view?usp=sharing

AIM:

To analysis the fluid flow over a NACA0017 air foil by varying the angle of attack as 0,2,4,6,8,10.

DIMENSTION:

Fluid=Air;

use NACA0017 Air foil

The number 0017 indicate the thickness

Velocity along X=Direction =500m/s

Air foil extruded=5mm

PROCEDURE:

Select the Insert option and choose the curve and Browse the NACA0017 air foil curve and fit it.
By using the option change entities change the curve into entities for sketching purpose
The NACA0017 air foil is not completely closed and so we use the line command to close the air foil.
If there is an requirement of tilting the air foil by chose the rotation command (In that first we select the whole area(spline and line) then select about which point it can be rotate and then give the tilting angle as negative foil tilted in downward direction)
Save the model and click the wizard.
In that we give some name to that analysis and then choose the external flow and then give the velocity input as 500m/s.
After the result compare the drag force and lifting force.And choose the Basic mesh
In order to get the accurate value of velocity profile chose the local mesh(refined mesh)along the surface of the air foil
And our goal is to compare the drag and lifting force.That is to click goal option in that we select the surface goals that is integreted force along X-axis is called the drag force and integrated force along Y-axis is called the lifting force.

After that we can compare the drag and lifting force by changing the angle of attack as 0,2,4,6,8,10.

AT 0 DEGREE ANGLE OF ATTACK:

velocity profile