I am doing some calculations for preliminary design of an airplane and I was wondering how I would go about determining the minimum thrust to weight ratio needed for the aircraft to takeoff. Which factors play a role and how are they limiting the thrust to weight ratio?
I admit the question is vague but it is intended to be that way. My team and I are tasked with building a Distributed Electric Propulsion based aircraft and the only other requisite apart from it being fully electric is that it must have a wingspan of at least 3 ft. Everything else is completely up to us to estimate and design.
I am looking for guidance on what factors I have to consider or what mathematical methods I would have to employ in order to estimate a necessary Thrust/Weight ratio