Flow over an airfoil
AIR FOIL FLOW:
An airfoil is a structure with curved surfaces designed to give the most favourable ratio of lift to drag in flight, used as the basic form of the wings, fins, and horizontal stabilizer of most aircraft
ANGLE OF ATTACK IN AIRFOIL:
The Angle of Attack is the angle at which relative wind meets an Aerofoil.
OBJECTIVE:
- To analyze the flow for NACA-0017 airfoil at various angles of attack and also to compare the lift and drag force.
- To perform the Flow Simulation at various angles of attack from 0° to 10° with an interval of 2° i.e. 0, 2, 4, 6, 8, 10°
- Also to perform Velocity distributions over NACA-0017 airfoil for different angles of attack.
- To plot and compare the Drag Force and Lift Force.
PROCEDURE:
3D MODEL:
Sketch part of Airfoil:
Extruded part of Airfoil:
BOUNDARY CONDITIONS AND VALUES:
Here Flow around an airfoil at various angles of attack (0, 2, 4, 6, 8, 10 degrees) are taken by the boundary condition and values that are provided below:
|
Input Conditions |
Values |
|
Analysis Type |
External Flow |
|
Fluids |
Air |
|
Units |
SI units |
|
Inlet Velocity |
600 m/s |
|
Chord Length |
1m |
|
Density |
1.225 kg/m^3 |
|
Time-Dependent |
Total analysis time: 5s Output Time step: 1s |
RESULTS:
Here, integrated force along the x-axis is taken as Drag force and integrated force along the y-axis is taken as Lift force.
CASE 1: Angle of attack at 0°
Drag force and Lift force
- Drag Force: 602.271 N
- Lift Force: -0.458 N
Cut Plot:
Summary:
Drag Force Plot:
Lift Force Plot:
CASE 2: Angle of attack 2°
Drag force and Lift force
- Drag Force: 664.97 N
- Lift Force: 1670.534 N
Cut Plot:
Summary:
Drag Force Plot:
Lift Force Plot:
CASE 3: Angle of attack 4°
Drag force and Lift force
Drag Force: 824.192 N
Lift Force: 3287.357 N
Cut Plot:
Summary:
Drag Force Plot:
Lift Force Plot:
CASE 4: Angle of attack 6°
Drag force and Lift force
Drag Force: 1104.292 N
Lift Force: 4889.511N
Cut Plot:
Summary:
Drag Force Plot:
Lift Force Plot:
CASE 5: Angle of attack 8°
Drag force and Lift force
Drag Force: 1511.100 N
Lift Force: 6498.261 N
Cut Plot:
Summary:
Drag Force Plot:
Lift Force Plot:
CASE 6: Angle of attack 10°
Drag force and Lift force
Drag Force: 1992.425 N
Lift Force: 8075.822 N
Cut Plot:
Summary:
Drag Force Plot:
Lift Force Plot:
COMPARISION STUDY:
|
Degree |
Avg Drag Force |
Avg Lift Force |
|
0 |
602.271 |
-0.458 |
|
2 |
664.97 N |
1670.534 |
|
4 |
824.192 |
3287.192 |
|
6 |
1104.292 |
4889.292 |
|
8 |
1511.100 |
6498.261 |
|
10 |
1992.425 |
8075.822 |
Comparison of Avg Drag Force:
Comparison of Avg Lift Force:
Drag force vs Lift Force:
CONCLUSION:
Here the following were observed during the above study process:
Also the constant value for drag and lift force was achieved in earlier iterations as the angle of attack increases.
For various angle of attacks, lift force was obtained as a linear curve without no deviations.
The drag is nearly constant at small angles (+/- 5 degrees) for the air foil
The increased frontal and increased boundary layer thickness causes the drag to rise as the angle increases above 5 degrees.
Thus the flow simulation of NACA-0017 air foil has been performed and the drag force and lift force plots are resulted.