Overview
The project had the goal of analyzing and recreating an airfoil based on the NACA number, and testing the airfoil in controlled conditions to see if it matched the characteristics of its full-scale counterparts. The airfoil chosen comes from the TP206E Turbo Super Skylane, with a NACA number of 2412. |
Cessna TP206E Turbo Super Skylane
The airfoil chosen comes from the airplane Cessna TP206E Turbo Skylane with a NACA number of 2512.These airplanes are also used for aerial photography, skydiving and other utility purposes. They can also be equipped with floats, floats and skis. Most often there used for luxury and personal purposes. |
Airfoil Data
Getting 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 Simulation
The 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. Complete
Foilsim Excel sheet
The 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. Complete
Foilsim Excel sheet
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.
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.
Test Results
Conclusion
1. Explain differences between the airfoil simulation prediction and the wind tunnel test results.
The differences between the airfoil simulation and windtunnel results are that both had different outcomes for the Lift and Drag.
2. What characteristic of the airfoil had the most significant impact on lift and drag?
The most significant thing that impacted the airfoil was how well designed and polished my airfoil was. If there were bumps or the airfoil wasn't sanded properly there would be significant differences on the lift and drag.
3. Explain what you would change in the design of your airfoil design?
What i would change in the airfoil design is how much time i took to make my airfoil since the more time and effort i take to carefully craft the airfoil. The better the airfoil would have been when it was in the wind tunnel.
The differences between the airfoil simulation and windtunnel results are that both had different outcomes for the Lift and Drag.
2. What characteristic of the airfoil had the most significant impact on lift and drag?
The most significant thing that impacted the airfoil was how well designed and polished my airfoil was. If there were bumps or the airfoil wasn't sanded properly there would be significant differences on the lift and drag.
3. Explain what you would change in the design of your airfoil design?
What i would change in the airfoil design is how much time i took to make my airfoil since the more time and effort i take to carefully craft the airfoil. The better the airfoil would have been when it was in the wind tunnel.