Flow over an NACA0010 airfoil

Objective: The following objectives are carried for a 0,2,4,6,8,10 angle of attack of a NACA0010 airfoil.

1. To model the flow over a NACA0010 airfoil.
2. To compare lift and drag forces at different angle of attacks.
3. To plot the velocity and pressure cross-sectional plots.

Assumptions:

1. Surface of aerofoil is smooth and roughness is considered zero.
2. The analysis is carried out at speed of 600 m/s.
3. Effect of supersonic velocity is not considered in study.
4. Fluid for flowing over aerofoil is considered to air having density of 1.2041 and Kinematic viscosity of 1.5111E-5 m2/sec.
5. Effects of temperature are not considered in study.

Procedure:

• The respective airfoil curve data is inserted in the solidworks.
• Wizard is launched with velocity over the airfoil in x-direction as 600m/s
• The computational domain is adjusted as per the requirement.
• The surface and global goals are set.
• The mesh is adjusted as per the requirement.
• Cutplots are inserted in the front view so as to look for the velocity and pressure plots and then the program is runned and the results are observed.
• A study is carried to compare the drag and lift force of the airfoil at the different angle of attacks.

Results:

For angle of attack= 0 degrees,

Velocity Distribution over aerofoil at zero angle of attack

Pressure Distribution over aerofoil at zero angle of attack

For angle of attack= 2 degrees

Velocity Distribution over aerofoil at two angle of attack

Pressure Distribution over aerofoil at two angle of attack

For angle of attack= 4 degrees,

Velocity Distribution over aerofoil at four angle of attack

Pressure Distribution over aerofoil at four angle of attack

For angle of attack= 6 degrees,

Velocity Distribution over aerofoil at six angle of attack

Pressure Distribution over aerofoil at six angle of attack

For angle of attack= 8 degrees,

Velocity Distribution over aerofoil at eight angle of attack

Pressure Distribution over aerofoil at eight angle of attack

For angle of attack= 10 degrees,

Velocity Distribution over aerofoil at ten angle of attack

Pressure Distribution over aerofoil at ten angle of attack

Tables and graphs:

Drag and Lift forces

Drag force vs Angle of attack

Lift force vs Angle of attack

Conclusion:

• Lift force increases with increase in angle of attack up to critical angle of attack after which it tends to decrease.
• Increasing the angle of attack results in increase in drag force and coefficient of drag due to increase in frontal area.
• At critical angle of attack flow separation occurs and it will lead to stalling.
• Lift at zero angle of attack is approximately zero for symmetrical aero foils.