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engine.pipeline.combustion_physics.CstarOfMR Class Reference

Public Member Functions

 __init__ (self, float Pc, Optional[CstarWideTable] wide=None, Any cea_cache=None)
Tuple[np.ndarray, np.ndarray] of_fraction (self, np.ndarray r)
float __call__ (self, float MR)

Public Attributes

 Pc = float(Pc)
str source = f"CEA c* table O/F {wide.MR_min:g}-{wide.MR_max:g} ({os.path.basename(wide.path or '')})"
 MR_lo
 MR_hi = wide.MR_min, wide.MR_max
 r_lo = self.MR_lo / (1.0 + self.MR_lo)
 r_hi = self.MR_hi / (1.0 + self.MR_hi)

Protected Member Functions

np.ndarray _in_range (self, np.ndarray mr)

Protected Attributes

 _lnMR = wide._lnMR
 _row = wide.row(self.Pc)
 _cache = None
 _c_lo = float(self._in_range(np.array([self.MR_lo]))[0])
 _c_hi = float(self._in_range(np.array([self.MR_hi]))[0])

Detailed Description

c*(O/F) at one chamber pressure, for ratios of c* between stream tubes.

One function serves numerator and denominator, so a perfectly mixed spray gives exactly 1.
Source, in order: the wide CEA table (O/F 0.1-20); else the design's CEA cache inside its O/F
range. Beyond either range the tube is the edge mixture diluted with unburned propellant:
with cp and molecular weight held, T0 and so c*^2 scale with the limiting propellant's
fraction, c* = c*_edge sqrt(r/r_edge) (fuel side) or sqrt((1 - r)/(1 - r_edge)) (oxidizer
side), r = O/(O + F). Against rocketcea for LOX/ethanol at 374 psia from the 1.0/2.5 edges this
is +8 % at O/F 0.7, -4 % at 0.3, -3 % at 3.0, -14 % at 6. Every use is recorded
(``outside``) so the caller can say how much mass rode on it.

Definition at line 313 of file combustion_physics.py.

Constructor & Destructor Documentation

◆ __init__()

engine.pipeline.combustion_physics.CstarOfMR.__init__ ( self,
float Pc,
Optional[CstarWideTable] wide = None,
Any cea_cache = None )

Definition at line 326 of file combustion_physics.py.

Member Function Documentation

◆ __call__()

float engine.pipeline.combustion_physics.CstarOfMR.__call__ ( self,
float MR )

Definition at line 363 of file combustion_physics.py.

References of_fraction().

◆ _in_range()

np.ndarray engine.pipeline.combustion_physics.CstarOfMR._in_range ( self,
np.ndarray mr )
protected

Definition at line 345 of file combustion_physics.py.

References _cache, _lnMR, engine.pipeline.combustion_physics.CstarWideTable._lnMR, _row, engine.pipeline.cea_cache.CEAAuxTables.Pc, Pc, and engine.pipeline.combustion_physics.CstarWideTable.Pc.

Referenced by of_fraction().

◆ of_fraction()

Tuple[np.ndarray, np.ndarray] engine.pipeline.combustion_physics.CstarOfMR.of_fraction ( self,
np.ndarray r ) 
c* at oxidizer mass fractions r = O/(O+F) in [0, 1]; returns (c*, outside-range mask).

Definition at line 350 of file combustion_physics.py.

References _c_hi, _c_lo, _in_range(), MR_hi, MR_lo, r_hi, and r_lo.

Referenced by __call__().

Member Data Documentation

◆ _c_hi

engine.pipeline.combustion_physics.CstarOfMR._c_hi = float(self._in_range(np.array([self.MR_hi]))[0])
protected

Definition at line 343 of file combustion_physics.py.

Referenced by of_fraction().

◆ _c_lo

engine.pipeline.combustion_physics.CstarOfMR._c_lo = float(self._in_range(np.array([self.MR_lo]))[0])
protected

Definition at line 342 of file combustion_physics.py.

Referenced by of_fraction().

◆ _cache

engine.pipeline.combustion_physics.CstarOfMR._cache = None
protected

Definition at line 335 of file combustion_physics.py.

Referenced by _in_range().

◆ _lnMR

engine.pipeline.combustion_physics.CstarOfMR._lnMR = wide._lnMR
protected

Definition at line 332 of file combustion_physics.py.

Referenced by _in_range().

◆ _row

engine.pipeline.combustion_physics.CstarOfMR._row = wide.row(self.Pc)
protected

Definition at line 333 of file combustion_physics.py.

Referenced by feedtwin.engine.card.Table2D._column(), and _in_range().

◆ MR_hi

engine.pipeline.combustion_physics.CstarOfMR.MR_hi = wide.MR_min, wide.MR_max

Definition at line 334 of file combustion_physics.py.

Referenced by of_fraction().

◆ MR_lo

engine.pipeline.combustion_physics.CstarOfMR.MR_lo

Definition at line 334 of file combustion_physics.py.

Referenced by of_fraction().

◆ Pc

engine.pipeline.combustion_physics.CstarOfMR.Pc = float(Pc)

Definition at line 329 of file combustion_physics.py.

Referenced by _in_range(), test_combustion_stability_audit.TestNyquistAllCrossings.case(), test_combustion_stability_audit.TestNyquistAllCrossings.L_indep(), and engine.pipeline.stability.timelag.ChamberThermo.Pc_bar().

◆ r_hi

engine.pipeline.combustion_physics.CstarOfMR.r_hi = self.MR_hi / (1.0 + self.MR_hi)

Definition at line 341 of file combustion_physics.py.

Referenced by of_fraction().

◆ r_lo

engine.pipeline.combustion_physics.CstarOfMR.r_lo = self.MR_lo / (1.0 + self.MR_lo)

Definition at line 340 of file combustion_physics.py.

Referenced by of_fraction().

◆ source

str engine.pipeline.combustion_physics.CstarOfMR.source = f"CEA c* table O/F {wide.MR_min:g}-{wide.MR_max:g} ({os.path.basename(wide.path or '')})"

Definition at line 331 of file combustion_physics.py.

The documentation for this class was generated from the following file: