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.
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.
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.
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.
Avro Cf100 Facts
It was a Canadian Jet interceptor/fighter serving during the Cold War. Its manufacturer is Avro Canada and it has a NACA number of 0010. Its brother plane Avro cf103. It was used in from 1952 to 1981 and its designer was John Frost.
It was a Canadian Jet interceptor/fighter serving during the Cold War. Its manufacturer is Avro Canada and it has a NACA number of 0010. Its brother plane Avro cf103. It was used in from 1952 to 1981 and its designer was John Frost.
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 (0010) to set the shape of the airfoil. The first number (0) represents the camber, the last two digits (10) represents the thickness. The size of the simulate airfoil is the same as the test airfoil. 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.
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 (0010) to set the shape of the airfoil. The first number (0) represents the camber, the last two digits (10) represents the thickness. The size of the simulate airfoil is the same as the test airfoil. 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.
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
Wind Tunnel Results Foilsim app results
Conclusion
1. Explain differences between the airfoil simulation prediction and the wind tunnel test results.
The Differences between the airfoil simulation and the wind tunnel results are that both had different outcomes for the lift and the 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 i created and designed my airfoil.
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 i take to carefully make the airfoil. The better the airfoil would have been when it was in the wind tunnel.
1. Explain differences between the airfoil simulation prediction and the wind tunnel test results.
The Differences between the airfoil simulation and the wind tunnel results are that both had different outcomes for the lift and the 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 i created and designed my airfoil.
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 i take to carefully make the airfoil. The better the airfoil would have been when it was in the wind tunnel.