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Most of the performance calculations are associated with the flight in a vertical plane. This is a 2D flight description.
The assumptions are:
- The aircraft can be considered as a point mass
- The aircraft is represented by its CG
- All forces are lumped at the CG (no moments)
- The aircraft is traveling along a curved path in the vertical plane
V : velocity tangent to path
L = lift; D = Drag, W = weight, T = thrust
Flight path angle (angle of the velocity vector wrt horizontal) : γ
Angle between V and the zero-lift-line of wing (ZLL): α
Angle between thrust and horizontal : β
Equations of Flight in the vertical Plane (Newton's Law)
Equilibrium Flight in Vertical Plane
Velocity components
Equation along the Velocity direction (Flight path)
Equilibrium Flight in Vertical plane (assembled from above)
These are the equations that are used to compute aircraft performance
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