14  ⚑ Thrust

Thrust model based on a simplified two-shaft turbofan model.

from openap import Thrust
thrust = Thrust("A320")

14.0.1 Thrust(ac, eng=None, backend=None)

Initialize a thrust model for a specific aircraft and engine combination.

Parameter Type Description
ac str ICAO aircraft type (e.g., β€œA320”)
eng str, optional Engine type (e.g., β€œCFM56-5A3”). Default: aircraft’s default engine
backend MathBackend, optional Computation backend. Default: NumpyBackend

14.0.2 takeoff(tas, alt=0, dT=0)

Calculate total thrust at takeoff condition.

Parameter Type Unit Description
tas float kt True airspeed
alt float ft Runway altitude. Default: 0
dT float K ISA temperature deviation. Default: 0

Returns: Total thrust (N)

thrust.takeoff(tas=100, alt=0)
200722.99758761944

14.0.3 cruise(tas, alt, dT=0)

Calculate thrust at cruise condition.

Parameter Type Unit Description
tas float kt True airspeed
alt float ft Altitude
dT float K ISA temperature deviation. Default: 0

Returns: Total thrust (N)

thrust.cruise(tas=450, alt=35000)
46159.58086889595

14.0.4 climb(tas, alt, roc, dT=0)

Calculate thrust during climb.

Parameter Type Unit Description
tas float kt True airspeed
alt float ft Altitude
roc float ft/min Rate of climb
dT float K ISA temperature deviation. Default: 0

Returns: Total thrust (N)

thrust.climb(tas=250, alt=10000, roc=2000)
91946.25704312592

14.0.5 descent_idle(tas, alt, dT=0)

Calculate idle thrust during descent. Idle thrust is approximated as 7% of maximum available thrust.

Parameter Type Unit Description
tas float kt True airspeed
alt float ft Altitude
dT float K ISA temperature deviation. Default: 0

Returns: Total thrust (N)

thrust.descent_idle(tas=300, alt=20000)
6358.064951276059