Flow over an airfoil

Objective:

• Model the flow over a NACA0017 airfoil
• For the angle of attacks 0,2,4,6,8,10 compare the lift and drag forces

Procedure:

• Importing the co-ordinates of the airfoli (Insert -> Curve -> Curve through XYZ points ->bowse the file ->open-> ok)

• Converting into sketch (Front plane -> Sketch -> Select the airfoil -> Convert entities)

• Closing the airfoil by line tool

• Adding angle of attack (Move entities -> Rotate entities -> Select the spline and line -> Select rotation point -> Adding angle as negative -> Ok)

• Do boss extrude

Flow Simulation:

• Wizard

• Project naming

• Flow type External - Time dependent (Simulation time = 5 sec, Time step = 1 sec)

• Fluid-Air
• Type of flow -Laminar and turbulent

• Initial condition - Velocity in x direction = 600m/s

• Setting up computational domain (Changing 3D to 2D)

• Inserting Goals (Global goals - Force in X and Y direction, Friction force in X and Y direction)

• Inserting Goals (Surface goals - Select the surface -> Force in X and Y direction)

• Mesh(Mesh -> Insert local mesh -> Select the surface on top -> Refining cell -> 3)

• Run

Result:

• At 0

pressur velocity

Drag lift

• At 2

pressure velocity

Drag Lift

• At 4

Pressure Velocity

Lift Drag

• At 6

Pressure

Lift Drag

• At 8

pressure Velocity

Lift Drag

• At 10

Pressure Velocity

Drag Lift

Conclusion:

Calculted the AOA at various numbers