Yes - the motor thrust (force) vector

*F*, which aligns approximately with the aircraft z-axis, decomposed into vertical and horizontal components at a pitch

*θ*, solves for equilibrium in constant-velocity flight. Ignoring body aerodynamic lift, which is not large for a quadcopter:

*F* cos*θ = Mg*

*F *sin*θ* = -*D* = -*ku*²

where

*M* is the mass of the aircraft and

*D* is the horizontal drag, which goes roughly with the square of the airspeed,

*u*. Eliminating

*θ* ( since cos²

*θ* + sin²

*θ* = 1):

*F* = √(*M²g²* + *k²u*⁴)

Power,

*P*, is approximately related to thrust by

*P² *∝

*F³.*
That rather simplified approach gives the following dimensionless relationship between airspeed, motor thrust, power and pitch angle:

View attachment 35983