I am interested in the preliminary design of a regional aircraft that uses turboprops as the propulsion method.
Following considerable research online about propeller design (disk theory, BEM...) I am rather lost on where to start.
To put it short, what parameters must be considered when designing the propeller of a turboprop device?
I am mainly interested in obtaining an idea of how many blades would be required and the diameter of the prop.
I have obtained values for the engine power requirements, and from what I can gather the main reason to have an increased number of blades is due to the requirement of absorbing the power from the engine. The latter therefore implicating an increased solidity ratio.
Is the any standard formula/theory that can provide such answers?