The presentation should include the following information:
Aircraft: Pilatus (PC-12)
A. Main airfoil for your selected aircraft
· Stall AOA and associated CLmax
· Zero-lift AOA
· Comparison of your main airfoil to a symmetric airfoil
B. Resultant attribute discussions for your selected aircraft
· Calculated stall speed
· How does lift change with airspeed if a constant AOA and altitude are held? (provide specific examples using the correct formula’s)
· How does lift change with altitude if a constant AOA and airspeed are held? (provide specific examples using the correct formula’s)
· How do the required CL and AOA for your specific aircraft (at a specific weight) change with changes in airspeed? (provide specific examples using the correct formula’s)
· What happens if the required CL is larger than CLmax of your airfoil, and what speed regime is usually associated with that condition?
The key to answering some of the questions is to provide specific calculation examples for your aircraft that showcase the points made. This means you should use actual formulas and example numbers to prove your statements. There are various forms in which you could do so, including self-generated tables and graphs or comparisons of key cases (e.g., comparing a low, medium, and high-altitude case).
L = CL * * S * V2 / 295
You will notice that all such calculations are ultimately based on repeated but different applications of the lift equation. Therefore, in order to apply the lift equation, a couple of aspects about your aircraft have to be known (i.e., researched) or assumed (i.e., detailed in your explanations). These parameters include:
Wing configuration (may include wingspan, wing area, aspect ratio, average chord, etc. – keep in mind that the lift equation ultimately requires wing area to calculate with.)
The weight of the aircraft (probably somewhat assumed but should definitely fall between the empty and max weight of the aircraft)
In your PowerPoint presentation, list the wingspan, wing area, aspect ratio, average chord and any other parameters you use for the Lift Formula.