The subject for your project investigations will be a specific propeller-driven general aviation (GA) aircraft of your choice. However, to simplify some of the more complex matters, choices are restricted to single-engine, monoplane configurations (i.e., no twin-engine, no bi-plane, no jet).
To provide some ideas, consider the following example aircraft:
Cessna (150, 152, 162, 172, or 182)
Piper (Cub, SuperCub, Comanche, or Cherokee)
Cirrus (SR20 or SR22)
Beechcraft (Bonanza or T-6)
Mooney (M20)
Pilatus (PC-6, PC-7, PC-9, PC-12, or PC-21)
Diamond (DA-20, DA-40, or HK-36)
Vans (any RV)
etc
As a starting point and the minimum content to cover, a shortlist of considerations and discussion points are provided below and can be directly copied into your presentation.
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)
How does lift change with altitude if a constant AOA and airspeed are held? (provide specific examples)
How do the required CL and AOA for your specific aircraft (at a specific weight) change with changes in airspeed? (provide specific examples)
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. 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). 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)
