WK95
Well-Known Member
Design methods including Raymer's, Roskam's , and Nicolai's generally involve starting with a mission and specific requirements for performance and then determining the takeoff weight.
LSAs, on the other hand, generally don't have that sort of flexibility since the majority of two seater LSAs have a maximum takeoff weight of 1320lbs (assuming non-amphibious). There is also a maximum sea level speed of 120kts.
How then, does one approach the design of an LSA? Would I start from 1320lbs then estimate performance and throughout the process work to optimize and modify performance where needed (For example, to keep the max level speed less than 120 kts)?
How else might the process of designing an LSA differ from Part 23 aircraft? I'd imagine one major difference is that there would be somewhat more freedom and flexibility.
LSAs, on the other hand, generally don't have that sort of flexibility since the majority of two seater LSAs have a maximum takeoff weight of 1320lbs (assuming non-amphibious). There is also a maximum sea level speed of 120kts.
How then, does one approach the design of an LSA? Would I start from 1320lbs then estimate performance and throughout the process work to optimize and modify performance where needed (For example, to keep the max level speed less than 120 kts)?
How else might the process of designing an LSA differ from Part 23 aircraft? I'd imagine one major difference is that there would be somewhat more freedom and flexibility.
