Flow over an airfoil

AIM:-To analyze and compare the drag ,lift foreces for various angle of attack on NACA0017 air foil.

PRINCIPLE:-Air foil is a streamline body.It is used mostly in airtransporation vehicles so that lift can achieved,drag force is reduced.`When the air flows over a cylinder with velocity the air when it comes into contact with cylinder the air kinetic energy is suddenly drops to to zero and this energy converts to pressure energy because of which the flow takes place over the cylinder.Slowly the pressure energy coverts back to kinetic energy.If the body is not streamlined after this point the boundary layer gets seperated and a back pressure is created which drecreses the lift and increases the drag force.The point at which the kinetic enery becomes Zero there are called stagnation points.To increase the lift the body has to be streamlined.If thebody is not stramlined at higher velocity the boundary layer separation takes place and back presuure is created and vortexes occurs. More streamlined the foil is more is the more lift force generated`

OBJECTIVES OF THE BODY:-

1. Analyze the drag,lift forces for various angle of attack.
2. Compare the drag ,lift forces.

BODY OF THE CONTENT:-

CREATING 3-D model of NACA0017:-

1. Choose the part and click on insert ,select the curve option.
2. Now click
3. Now extrude to 0.2m long and save the file for flow stimulation.

FLOW STIMULATION:-

1. Click on flow wizard ,choose the flow fluid.
2. Choose time dependent option , give inlet velocity .
3. After completion of the above step enlarge the domain size.
4. Now choose global ,surface goals.
5. Make refinement of mesh by choosing local mesh.
6. Now run the stimulation.
7. Click on insert in solver and select preview,goals so that graphs ,flow over airfoil is visible.
8. Now run the animation,save plots and export them to EXCEL sheets.

 CUTPLOTS  FOR VARIOUS ANGLE OF ATTACK:-

VELOCITY FOR ANGLE OF ATTACK-0:-

PRESSURE FOR ANGLE OF ATTACK-0:-

VELOCITY FOR ANGLE OF ATTACK-2:-

PRESSURE FOR ANGLE OF ATTACK-2:-

VELOCITY FOR ANGLE OF ATTACK-4:-

PRESSURE FOR ANGLE OF ATTACK-4:-

VELOCITY FOR ANGLE OF ATTACK-6:-

PRESSURE FOR ANGLE OF ATTACK-6:-

VELOCITY FOR ANGLE OF ATTACK-8:-

PRESSURE FOR ANGLE OF ATTACK-8:-

VELOCITY FOR ANGLE OF ATTACK-10:-

PRESSURE FOR ANGLE OF ATTACK-10:-

DRAGFORCES FOR ANGLE OF ATTACK-0:-

LIFTFORCES FOR ANGLE OF ATTACK-0:-

DRAGFORCES FOR ANGLE OF ATTACK-2:-

LIFTFORCES FOR ANGLE OF ATTACK-2:-

DRAGFORCES FOR ANGLE OF ATTACK-4:-

LIFTFORCES FOR ANGLE OF ATTACK-4:-

DRAGFORCES FOR ANGLE OF ATTACK-6:-

LIFTFORCES FOR ANGLE OF ATTACK-6:-

DRAGFORCES FOR ANGLE OF ATTACK-8:-

LIFTFORCES FOR ANGLE OF ATTACK-8:-

DRAGFORCES FOR ANGLE OF ATTACK-10:-

LIFTFORCES FOR ANGLE OF ATTACK-10:-

COMPARISION OF DRAG FORCES:-

COMPARISION OF LIFT FORCES:-

INFERENCES FROM THE CUTPLOTS,GRAPHS:-

1. From the cutplots of pressure we can observe that as angle of attack is increased  the pressure is also increased.
2. From the cutplots of velocity we can observe that as angle of attack is increased  the pressure is also increased.
3. As the angle of attack increases the drag forces tend to increases by considerable amounts.
4. As the angle of attack increases the drag forces tend to increases drastically.
5. For negative angle of attack is use when to increase the lift in upward direction.
6. For positive angle of attack is use when to increase the lift in downward direction.

CONCLUSION:-

1. Created 3-D model of NACA0017 airfoil.
2. Performed flow stimulation for angle of attack-0,2,4,6,8,10.
3. Obtained cutplots for velocity ,pressure for  angle of attack-0,2,4,6,8,10.
4. Compared the drag forces ,lift forces.