Overview- The project goal is to analyze and recreate an airfoil based on the NACA number. Then test and record the airfoil in simulated conditions. Then create an airfoil and test it to see if it matched the characteristics of its simulated counterparts.
Plane Name- Aeronca 11-AC Chief NACA 4412
Manufacturer- Aeronca
Uses-Light utility aircraft
The NACA four-digit wing sections define the profile by:
- First digit describing maximum camber as percentage of the chord.
- Second digit describing the distance of maximum camber from the airfoil leading edge in tens of percents of the chord.
- Last two digits describing maximum thickness of the airfoil as percent of the chord
The airfoil was put into a wind tunnel and tested from -20 degrees Angle of Attack to +20 degrees Angle of Attack at 5 degree increments. Before testing, the same experiment was performed using the NASA Foilsim app set to the exact same conditions to calculate the lift/drag coefficient. Since it is a ratio, the scaling of the airfoil should have no effect on the outcome. |