I'm working on designing an aircraft with some specific requirements (Vstall, Vmax, Ceiling, Payload, Range, RoC, Slanding/takeoff etc).
I'm following Anderson's and Raymer's ways (trying to find the best for me).
Right now I'm stuck at the step of estimating for the first time the Wing Loading (W/S). Doing the calculations about the W/S constraints (Vstall, Landing distance from Anderson) I found that the Stall constraint is very strict. The result that I get is a W/S = 24 lb/ft2 for a twin turboprop with a estimated gross takeoff weight of 16k lbs. The constraint of landing distance gives a W/S of 62.
Looking at historical data (and some similar aircraft) and Raymer's/Anderson's tables the W/S = 24 is way off the ordinary values. I do understand that it is just an estimation.
What would you suggest to do so I can satisfy the requirement and be able to get a higher W/S?
I thought about changing the flaps that I used (Split Flap) but I don't know if it's possible and realistic to have "Double Slotted Flaps and Slats" for a simple twin turboprop that has a simple mission.
edit: After the comment, here are the equations about the Vstall and Landing Distance.