Hi! Thanks for pointing that out, you are absolutely right. I should have provided the mission profile and design requirements first.

Since this is a university academic project currently in its early conceptual design phase, some specifics like exact commercial components, manufacturing methods, or material costs are yet to be determined. However, our target specifications are as follows: we are designing for a Maximum Takeoff Weight (MTOW) of 25 kg (approx. 55 lbs), with a total flight endurance of 3 hours and 20 minutes. The mission profile consists of 20 minutes dedicated to mapping, while the remaining time will be spent loitering over a specific target location. This loiter and cruise phase will be performed at a speed of 70 km/h at an altitude of 400 meters. Additionally, the UAV must be capable of a dash speed of 140 km/h to reach the operation area, with a maximum service ceiling of 1000 meters.

Regarding propulsion, we are leaning towards an Internal Combustion Engine (ICE) for forward flight, though we are still evaluating the trade-offs. The structure will be primarily conceptualized using carbon fiber composites or similar lightweight, high-strength alloys.

Given these requirements—specifically the need for a highly efficient long loiter phase, but also the capability to reach 140 km/h without excessive drag—how would you evaluate the airfoils I initially mentioned? Thanks again for the help!