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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:

  1. Rotor parameters

         number of rotors
         Rotor diameter
         rpm
         number of blades
    
  2. 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.

  3. The VTOL is a tilt rotor type with ducted fans
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  • $\begingroup$ Are your rotors ducted or unducted? What kind of VTOL is this? Depending on the specific configuration, the transition and cruise phases would need to consider the disk loading like in a helicopter. If, however, the wing is large and the disk surface is negligible, then you can treat the rotors as vectored thrust sources and just use high school trigonometry to solve the transitory phase. $\endgroup$ – AEhere Feb 11 at 9:08
  • $\begingroup$ Ok let's say I assume my wing to be large and disk area negligible.....How do I calculate the power now?....Because I feel integration is involved from 0 deg to 90 deg. $\endgroup$ – sai teja Feb 11 at 10:49

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