Flow Simulation On Airfoil Using Solidworks
Introduction
An airfoil is the term used to describe the cross-sectional shape of an object that, when moved through a fluid such as air, creates an aerodynamic force. Aerofoils are employed on aircraft as wings to produce lift or as propeller blades to produce thrust. Both these forces are produce perpendicular to the air flow. Drag is a consequence of the production of lift/thrust and acts parallel to the airflow.
The basic principle behind an airfoil is described by bernoullis theorem. Basically this states that total pressure is equal to static pressure (due to the weight of air above) plus dynamic pressure (due to the motion of air).
Air that travels over the top surface of the aerofoil has to travel faster and thus gains dynamic pressure. The subsequent loss of static pressure creates a pressure difference between the upper and lower surfaces that is called lift and opposes the weight of an aircraft (or thrust that opposes drag).
As the angle of attack (the angle between the chord line and relative air flow) is increased, more lift is created. Once the critical angle of attack is reached the aerofoil will stall.
This Project shows the effect of air on airfoil at different angle of attack.
Steps
1.NACA 0017 Codes are generated from air foil 4-digit generator and saved as .txt format.
2.Open new part design in solidworks and insert curve with the given coordinates.
3.Convert the entities and rotate with various angle of attacks ranging from 0,2,4,6,8,10 and save the given data.
4.Open flow simulation and apply external flow and time dependant function after that apply velocity in X-direction.
5.Run the simulation and compare the drag and lift properties with different angle of attacks.
For 0 Degree Angle of Attack
DRAG
LIFT
VALUES
For 2 Degree Angle of Attack
DRAG
LIFT
VALUES
For 4 Degree Angle of Attack
DRAG
LIFT
VALUES
For 6 Degree Angle of Attack
DRAG
LIFT
VALUES
For 8 Degree Angle of Attack
DRAG
LIFT
VALUES
For 10 Degree Angle of Attack
DRAG
LIFT
VALUES