from openap import FuelFlow16 π₯ FuelFlow
Fuel flow model based on the ICAO emission databank.
16.0.1 FuelFlow(ac, eng=None, backend=None)
| Parameter | Type | Description |
|---|---|---|
ac |
str |
ICAO aircraft type (e.g., βA320β) |
eng |
str, optional |
Engine type. Default: aircraftβs default engine. |
backend |
MathBackend, optional |
Computation backend. Default: NumpyBackend. |
fuelflow = FuelFlow("A320")16.0.2 enroute(mass, tas, alt, vs=0, acc=0, dT=0, limit=True)
Compute fuel flow during climb, cruise, or descent (clean configuration, no flaps/gear).
| Parameter | Type | Unit | Description |
|---|---|---|---|
mass |
float/array | kg | Aircraft mass |
tas |
float/array | kt | True airspeed |
alt |
float/array | ft | Altitude |
vs |
float/array | ft/min | Vertical rate. Default 0. |
acc |
float/array | m/sΒ² | Acceleration. Default 0. |
dT |
float/array | K | ISA temperature deviation. Default 0. |
limit |
bool | β | Apply thrust limits. Default True. |
Returns: Fuel flow (kg/s)
fuelflow.enroute(mass=60000, tas=250, alt=30000)0.784807657215608216.0.3 takeoff(tas, alt=None, throttle=1)
Compute fuel flow at takeoff.
| Parameter | Type | Unit | Description |
|---|---|---|---|
tas |
float/array | kt | True airspeed |
alt |
float/array | ft | Airport altitude. Default: sea level. |
throttle |
float/array | β | Throttle setting, 0 to 1. Default 1 (full thrust). |
Returns: Fuel flow (kg/s)
fuelflow.takeoff(tas=100, alt=0)2.146718038132166716.0.4 at_thrust(total_ac_thrust)
Compute fuel flow at a given total aircraft thrust.
| Parameter | Type | Unit | Description |
|---|---|---|---|
total_ac_thrust |
float/array | N | Total net thrust |
Returns: Fuel flow (kg/s)
fuelflow.at_thrust(total_ac_thrust=50000)1.030994449223533716.0.5 plot_model(plot=True)
Plot the engine fuel model.
| Parameter | Type | Description |
|---|---|---|
plot |
bool | Display plot or return pyplot object. Default True. |
fuelflow.plot_model()