RCAIDE.Library.Methods.Powertrain.Converters.Compression_Nozzle.compute_compression_nozzle_performance
compute_compression_nozzle_performance#
- compute_compression_nozzle_performance(compression_nozzle, conditions)[source]#
Computes the performance of a compression nozzle based on its polytropic efficiency.
- Parameters:
compression_nozzle (Data) –
- Data dictionary with compression nozzle properties
- tagstr
Identifier for the compression nozzle
- pressure_ratiofloat
Pressure ratio across the nozzle [unitless]
- polytropic_efficiencyfloat
Polytropic efficiency of the nozzle [unitless]
- pressure_recoveryfloat
Pressure recovery factor [unitless]
- compressibility_effectsbool
Flag to include compressibility effects
- working_fluidData
Working fluid object with methods to compute properties
conditions (Data) –
- Data dictionary with flow conditions
- freestreamData
Freestream flow properties - pressure : ndarray
Freestream pressure [Pa]
- mach_numberndarray
Freestream Mach number [unitless]
- energyData
- Energy conditions
- convertersdict
Dictionary of converter conditions indexed by tag - inputs : Data
Input conditions - stagnation_temperature : ndarray
Entering stagnation temperature [K]
- stagnation_pressurendarray
Entering stagnation pressure [Pa]
- static_temperaturendarray
Entering static temperature [K]
- static_pressurendarray
Entering static pressure [Pa]
- mach_numberndarray
Entering Mach number [unitless]
- Returns:
- Results are stored in conditions.energy.converters[compression_nozzle.tag].outputs:
- stagnation_temperaturendarray
Exit stagnation temperature [K]
- stagnation_pressurendarray
Exit stagnation pressure [Pa]
- stagnation_enthalpyndarray
Exit stagnation enthalpy [J/kg]
- mach_numberndarray
Exit Mach number [unitless]
- static_temperaturendarray
Exit static temperature [K]
- static_enthalpyndarray
Exit static enthalpy [J/kg]
- velocityndarray
Exit nozzle velocity [m/s]
- static_pressurendarray
Exit static pressure [Pa]
- Return type:
None
Notes
This function computes the thermodynamic properties at the exit of a compression nozzle based on the inlet conditions and nozzle characteristics. It handles both subsonic and supersonic flows with appropriate relations.
- Major Assumptions
Pressure ratio and polytropic efficiency do not change with varying conditions
Adiabatic process
Subsonic or choked output
Theory The compression nozzle performance is calculated using gas dynamics relations for compressible flow. For subsonic flow, isentropic relations are used. For supersonic flow, normal shock relations are applied. The stagnation properties are transformed to static properties based on the exit Mach number.
References
[1] Stanford University, “AA283 Course Notes”, https://web.stanford.edu/~cantwell/AA283_Course_Material/AA283_Course_Notes/