OverviewThe 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. |
EV-97A FactsLight sport aircraft (LSA), manufactured by Evektor-Aerotechnik of the Czech Republic and powered by a Rotax
912ULS, 100 horsepower engine. |
Airfoil DataGetting the vital data based on the NACA number
involved looking up the NACA number for the chosen airfoil, and plotting its profile. We used the NACA 4 digit series profile generate to get the profile. This profile is used to create the airfoil for testing. |
Airfoil SimulationThe NASA FoilSim applet calculates the lift of an
airfoil based on user inputs of flow conditions and wing geometry. We used the NACA number (4412) to set the shape of the airfoil. The first number (4) represents the camber, the last two digits (12) represents the thickness. The size of the simulate airfoil is the same as the test airfoil (4" chord and 4" span). The flight conditions are set at 60 mph and the altitude is at 0. The data is recorded with the Angle of Attack is set to -20 and the Final Angle of Attack to 20 and the Angle of Attack Step to 5 degrees. Complete Foilsim Excel chart is below. |
Construction
Construction of the airfoil was acheived by
sandwiching 2 inches of foam between identical airfoil cross-sections made of
3/16" plywood. The foam was then cut out and sanded to match the
cross-sections, and then the cross sections were removed and mounting clip was
attatched. The scaled profile of the airfoil were used to create the
cross-section pieces that served as the guideline for the airfoil itself.
sandwiching 2 inches of foam between identical airfoil cross-sections made of
3/16" plywood. The foam was then cut out and sanded to match the
cross-sections, and then the cross sections were removed and mounting clip was
attatched. The scaled profile of the airfoil were used to create the
cross-section pieces that served as the guideline for the airfoil itself.
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. |