Flow over an airfoil
Aim :
To design NACA0017 airfoil with given data and to perform parameteric study on ( Angle of attack ) vs ( Lift force and Drag force )
Introduction :
NACA - National Advisory committee for Aeronautics has developed Airfoil design for aircraft wings.
Series
1. 4 - digit series
2. 5 - digit series
3. 6 - digit series
4. 7- digit series
5. 8 - digit series
6. 1-series
Nomenclature of NACA airfoil:
1. Leading edge
2. Trailing edge
3. Thickness
4. Camber
5. Mean camber line
6. Chord
7. Chord line
TYPES OF AIRFOIL:
1. Symmetric airfoil - both upper and lower curvature is same
2. Cambered Airfoil
Theory :
Angle of attack ( AOA ) is the angle between free stream velocity and leading edge of airfoil. Coefficient Of Lift ( C.L) will increase as AOA increases upto Critical Angle of attack. After which Drag force will increase abruptly. This is due to Flow separation phenomena which occurs on low pressure side of airfoil. As we know Lift force is generated along High pressure to Low pressure direction.
NACA 0017 means - Symmetric airfoil with Maximum thickness of airfoil is 17% of the chord length.
COMMON SETTINGS:
Velocity along X direction : 800 m/s
Local MESH SIZE : 4 @ longer surface of airfoil
BASIC MESH SIZE : 4
FLOW FIELD length :
Angle of Attack : 0 degree
Pressure distribution:
Velocity distribution:
Result:
Angle of Attack : 2 degree
Pressure distribution:
Velocity distribution:
Result:
Angle of Attack : 4 degree
Pressure distribution:
Velocity distribution:
Result:
Angle of Attack : 6 degree
Pressure distribution:
Velocity distribution:
Result:
Angle of Attack : 8 degree
Pressure distribution:
Velocity distribution:
Result:
Angle of Attack : 10 degree
Pressure distribution:
Velocity distribution:
Result:
CONSOLIDATED RESULT:
| Angle of Attack | Lift Force | Drag Force |
| 0 | 29N | 1127 N |
| 2 | 2206 N | 1195 N |
| 4 | 4365 N | 1408 N |
| 6 | 6525 N | 1788 N |
| 8 | 8682 N | 2366 N |
| 10 | 10852 N | 3025 N |
Results:
As AOA increases corresponding Lift Force generated keeps increasing.