In a VTOL, I have calculated the power required for take off and cruise which was not difficult at all. Between take off and cruise, there is a phase where the VTOL has to transition by tilting the rotors from 0 to 90 deg. I am finding it hard to calculate the power required for this transition. I feel this is very important because it consumes more power than take off since it is creating lift (hasn't reached the minimum velocity for the lift requirement) for balancing weight and also needs to provide thrust for forward motion. Given to me are:
number of rotors Rotor diameter rpm number of blades
Fixed wing parameters
span and chord (rectangular wing) lift and drag coefficients
What are the factors considered to calculate the power required for transition? Please note: Make as many assumptions/approximation as you like .I just want a simple formula for a basic understanding.
- The VTOL is a tilt rotor type with ducted fans