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.
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
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.
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.
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
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 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.
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 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.
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.
-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.
Conclusion
1. Explain differences between the airfoil simulation prediction and the wind tunnel test results.
With wind there is an actual physical effect on the airfoil.
2. What characteristic of the airfoil had the most significant impact on lift and drag?
3. Explain what you would change in the design of your airfoil design?
1. Explain differences between the airfoil simulation prediction and the wind tunnel test results.
With wind there is an actual physical effect on the airfoil.
2. What characteristic of the airfoil had the most significant impact on lift and drag?
3. Explain what you would change in the design of your airfoil design?