RCAIDE.Library.Methods.Powertrain.Converters.Supersonic_Nozzle.compute_supersonic_nozzle_performance
compute_supersonic_nozzle_performance#
- compute_supersonic_nozzle_performance(supersonic_nozzle, conditions)[source]#
Computes the performance parameters of a supersonic nozzle based on input conditions.
- Parameters:
supersonic_nozzle (RCAIDE.Components.Energy.Converters.Supersonic_Nozzle) – The supersonic nozzle component for which performance is being computed
conditions (RCAIDE.Framework.Mission.Common.Conditions) – Container for flight conditions and energy system states
- Returns:
This function modifies the conditions object in-place
- Return type:
None
Notes
This function calculates output values from input conditions according to gas dynamics equations for supersonic nozzles.
- Major Assumptions
Constant polytropic efficiency and pressure ratio
Isentropic flow except for losses accounted by efficiency terms
Perfect gas behavior
Theory
The nozzle performance is calculated using isentropic flow relations. For supersonic flow, the Mach number is calculated from the pressure ratio:
\[M = \sqrt{\frac{2}{\gamma-1}\left[\left(\frac{P_t}{P_0}\right)^{\frac{\gamma-1}{\gamma}}-1\right]}\]The static temperature is related to stagnation temperature by:
\[T = \frac{T_t}{1+\frac{\gamma-1}{2}M^2}\]Definitions
- ‘Pressure ratio’
Ratio of exit pressure to inlet pressure in the nozzle
- ‘Polytropic efficiency’
Measure of the nozzle’s thermodynamic efficiency accounting for irreversibilities
References
[1] Cantwell, B. “AA283 Course Material: Course Notes.” Stanford University. https://web.stanford.edu/~cantwell/AA283_Course_Material/AA283_Course_Notes/