Flow over an airfoil

FLOW OVER AIRFOIL
AIM
To model the flow over a NACA0017 airfoil for angle of attacks 0,2,4,6,8,10 and compare the lift and drag forces

AIRFOIL
An airfoil is a cross sectional shape od wings, propeller etc. They produce aerodynamic forces. The two components of forces are lift and drag. Here we are analysing NACA0017 airfoil.

SIMULATION
Create the Airfoil part as per given.
Do flow simulation while defining thee correct computational domians.
Analyse the result of pressure, velocity contours.
Analyse the lift and drag force obtained each cases of for angle of attacks 0,2,4,6,8,10.

PART

https://drive.google.com/drive/folders/1dma8yOIeRqWnRpIdEmLfb_BKSLteKkfl?usp=sharing

PLOTS
AOA 0 degree
Pressure

Velocity

Result

AOA 2 degree
Pressure

Velocity

Result

AOA 4 degree
Pressure

Velocity

Result

AOA 6 degree
Pressure

Velocity

Result

AOA 8 degree
Pressure

Velocity

Result

AOA 10 degree
Pressure

Velocity

Result

FINAL

RESULT
We observed that as AOA increases, the lift forces increase linearly and drag forces increases non linerly.
It is also observed that there is only small lift produced in 0 degree angle of attack.
The maximum L/D ratio is observed at 6 degree.