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 AAI Shadow 200
This plane is an unmanned aerial vehicle which is used for reconnaissance, surveillance, target acquisition, and assessments of battle damage. It is in use by the United States Army, Marine Corps, Australian Army, and Swedish Army. The plane was developed from the RQ-2 Pioneer and uses the high-wing design.
The NACA 4-Digit Series
NACA- 4415
The first digit, 4, determines that 4% is the maximum camber of the chord
The second digit, 4, is the distance of maximum camber from the airfoil leading edge in tens percents of the chord
The third digit, 1, and the fourth digit, 5, determines that the maximum thickness of the chord is 1% and 5%
The NACA 4415 has a maximum camber of 4% which is 40% away from the leading edge with a maximum depth of 15% of the chord.
The first digit, 4, determines that 4% is the maximum camber of the chord
The second digit, 4, is the distance of maximum camber from the airfoil leading edge in tens percents of the chord
The third digit, 1, and the fourth digit, 5, determines that the maximum thickness of the chord is 1% and 5%
The NACA 4415 has a maximum camber of 4% which is 40% away from the leading edge with a maximum depth of 15% of the chord.
Data from Wind Tunnel
There are many differences in the data I collected with the wind tunnel and the information provided by NASA. My numbers are generally higher and not within range of the numbers from the other program.
1. Explain differences between the airfoil simulation prediction and the wind tunnel test results.
There was a big difference in the results I obtained from the wind tunnel and the NASA program. My numbers had a lot of variation and followed the pattern of increasing in Cd, lift, and drag as the angle increased.
2. What characteristic of the airfoil had the most significant impact on lift and drag?
The angle of the front of the airfoil would have the biggest impact because it correlates directly with the aerodynamics of it as a whole.
3. Explain what you would change in the design of your airfoil design?
I would make the front of the airfoil thinner to have better aerodynamics.