Climb performance

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The climb performance describes the ability of an aircraft to climb to a certain altitude in a certain time. The time required for this is the rise time .

The power corresponds to the maximum rate of climb and is specified in meters per second (m / s) or feet per minute (ft / min).

A certain climbing angle and a certain flight speed are assigned to a maximum climbing performance . The climb performance depends on the thrust-to-weight ratio , i. H. engine performance, aircraft weight , external conditions (e.g. hot and high ) and other factors. With increasing flight altitude , the climb performance decreases continuously due to decreasing engine power and lower air density ( peak altitude ).

Vertical speed in m / s: ${\displaystyle v_{y}}$

${\displaystyle v_{y}={\frac {75\cdot P\cdot \eta _{L}}{m}}-c_{w}\cdot {\sqrt {\frac {2\cdot g\cdot m}{\rho \cdot A\cdot c_{a}\,^{3}}}}}$

With

• ${\displaystyle P}$ Engine power in  hp
• ${\displaystyle \eta _{L}}$ Air screw efficiency
• ${\displaystyle m}$ Aircraft mass in kg
• ${\displaystyle c_{w}}$ Drag coefficient aircraft
• ${\displaystyle g}$ Gravitational acceleration = 9.81 m / s ²
• ${\displaystyle \rho }$ Air density in kg / m³
• ${\displaystyle c_{a}}$ Lift coefficient for minimal sinking
• ${\displaystyle A}$ Wing area in m²

literature

• Wilfried Copenhagen: Transpress Lexicon Aviation . 4th, revised edition. Transpress, Berlin 1979, p. 529 .

Individual evidence

1. ^ Heinz A. F. Schmidt: Meyers Taschenlexikon: Aviation . 2nd improved and enlarged edition. Bibliographisches Institut, Leipzig 1967, p. 320 .