We assume in this tutorial that the goal is to design an light sport aircraft (EASA CS-23) with the following specifications:
- A minimum cruise speed of 140 knots
- A span of 8 meters or less
- A fuel capacity of approx. 160 l
- Two comfortable seats in tandem, passengers and cargo weight approx. 500 lbs / 227 kg
- Can make a trip with maximum payload from Paris to Stockholm (1600km) in less than 10 hours
- A 160 hp engine with constant speed propeller
- A stall velocity under of 50 kn with flaps, and under 55 kn without flaps.
We suppose that the NACA 23012 airfoil was selected to be the main airfoil. We also assume that the empty mass of the aircraft has been estimated at 838 lbs / 380 kg. Adding 160 liters of fuel and passengers and payload, the max take-off mass is estimated at 1610 lbs / 730 kg.
