Flow over an airfoil
Aim:
To Model the flow over a NACA0017 airfoil and For the angle of attacks 0,2,4,6,8,10 compare the lift and drag forces.
Airfoil used:
NACA0017 AIRFOIL
Data used:
https://drive.google.com/file/d/1-pt5EubuTwfgpMWicEQSR05FQaXurYXx/view?usp=sharing
Description:
Airfoil:
An airfoil-shaped body moving through a fluid produces an aerodynamic force. The component of this force perpendicular to the direction of motion is called lift. The component parallel to the direction of motion is called drag. subsonic flight airfoils have a characteristic shape with a rounded leading edge, followed by a sharp trailing edge, often with a symmetric curvature of upper and lower surfaces. Foils of similar function designed with water as the working fluid are called hydrofoils.
S
NACA airfoils:
The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). The shape of the NACA airfoils is described using a series of digits following the word "NACA". The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties
Simulation:
A simulation is an approximate imitation of the operation of a process or system that represents its operation over time.
Lift:
The lift generated at the airfoil is primarily due to the angle of attack, as we change the angle of attack the lift force experienced by the airfoil changes. A fluid flowing around the surface of an object exerts a force on it. Lift is the component of this force that is perpendicular to the oncoming flow direction.
Drag :
The drag force at the airfoil acts parallel to the direction of the motion of the airfoil. with the changing angle of attacks the drag force acting also keeps changing. Drag is a force acting opposite to the relative motion of any object moving with respect to a surrounding fluid.
Solid works model:
Mesh:
Case 1:
when the angle of attack is at 0 degrees:
Velocity :
pressure:
Lift and drag force:
avg Drag:75.4562N
avg lift:45.421N
Case 2:
when the angle of attack is at 2 degrees:
Velocity :
pressure:
Lift and drag force:
avg Drag:87.7741N
avg lift:190.5278N
Case 3:
when the angle of attack is at 4 degrees:
Velocity :
pressure:
Lift and drag force:
avg Drag:105.4527N
avg lift:394.752N
Case 4:
when the angle of attack is at 6 degrees:
Velocity :
pressure:
Lift and drag force:
avg Drag:137.505N
avg lift:556.547N
Case 5:
when the angle of attack is at 8 degrees:
Velocity :
pressure:
Lift and drag force:
avg Drag:179.0994N
avg lift:775.475N
Case 6:
when the angle of attack is at 10 degrees:
Velocity :
pressure:
Lift and drag force:
avg Drag:356.151N
avg lift:1852.875N
Final output:
Result:
From the above results,
1. With the increase in angle of attack, the generated lift force also increases until the stalling condition is reached after which it starts to decrease.
2. Similarly, Drag force also increases with the increase in the angle of attack as more surface gets exposed to the flowing fluid.
3. With the increase in angle of attack, the airfoil separates and develops a pressure gradient with the frontal area with higher and the dorsal area with lower pressure. Thus generating higher drag and lift force.