RCAIDE.Library.Methods.Powertrain.Converters.Engine.compute_power_from_throttle
compute_power_from_throttle#
- compute_power_from_throttle(engine, conditions)[source]#
Computes engine power output and performance metrics based on throttle setting and atmospheric conditions.
- Parameters:
engine (RCAIDE.Library.Components.Propulsors) –
- Engine instance with the following attributes:
- sea_level_powerfloat
Maximum power output at sea level [W]
- flat_rate_altitudefloat
Altitude below which power remains constant [m]
- power_specific_fuel_consumptionfloat
Power specific fuel consumption [kg/(W·s)]
engine_conditions (RCAIDE.Framework.Mission.Common.Conditions) –
- Engine operating conditions with:
- throttlenumpy.ndarray
Throttle setting [dimensionless]
- speednumpy.ndarray
Engine angular velocity [rad/s]
conditions (RCAIDE.Framework.Mission.Common.Conditions) –
- Flight conditions with:
- freestream.altitudenumpy.ndarray
Current altitude [m]
- freestream.delta_ISAnumpy.ndarray
Temperature offset from standard atmosphere [K]
- Return type:
None
Notes
Power available is computed using the Gagg and Ferrar model, which accounts for atmospheric density effects on engine performance.
- Major Assumptions
Power varies linearly with density ratio above flat-rate altitude
Power remains constant below flat-rate altitude
Standard atmosphere conditions apply except for ISA temperature offset
Minimum power output is zero (negative values are clipped)
Power is directly proportional to throttle setting
Theory
The power available is computed using:
\[P_{available} = P_{SL} \frac{\sigma - 0.117}{0.883}\]- where:
\(P_{SL}\) is sea-level power
\(\sigma\) is the density ratio
References
[1] Gudmundsson, S. (2014). General Aviation Aircraft Design: Applied Methods and Procedures. Butterworth-Heinemann. [2] Gagg and Ferrar