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.
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AT-501 Facts The airfoil chosen comes from the Airtractor AT-501, with a NACA number
of 4415.The Airtractor AT-501 is use for agricultural crop dusting, it is made by Airtractor inc and it is a monoplane low wing taildragger (see picture above). |
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 (4415) to set the shape of the airfoil. The first number (4) represents the camber, the last two digits (15) 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. ConstructionConstruction 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. |
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.
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.
Test Results
Conclusion
1. Explain differences between the airfoil simulation prediction and the wind tunnel test results.
The wind tunnle info was a bit different and a little more accurate.
2. What characteristic of the airfoil had the most significant impact on lift and drag?
the angle of the airfoil made the drag increase or decrease.
3. Explain what you would change in the design of your airfoil design?
I would have done a better job sanding and making it more smooth.