| __init__(self, *, float mass_kg, float reference_area_m2, float nozzle_exit_area_m2, float elevation_m, Optional[float] reference_pressure_pa, Any drag=None, float dt_max=0.01) | engine.layerx.flight.InlineAscent | |
| _cd_off | engine.layerx.flight.InlineAscent | protected |
| _cd_on | engine.layerx.flight.InlineAscent | protected |
| _integrate(self, float t0, float t1, float f0, float f1, float md0, float md1) | engine.layerx.flight.InlineAscent | protected |
| _isa | engine.layerx.flight.InlineAscent | protected |
| _mach | engine.layerx.flight.InlineAscent | protected |
| _rhs(self, float z, float v, float m, float thrust, float mdot) | engine.layerx.flight.InlineAscent | protected |
| _specific(self, float z, float v, float m, float thrust) | engine.layerx.flight.InlineAscent | protected |
| A_e | engine.layerx.flight.InlineAscent | |
| A_ref | engine.layerx.flight.InlineAscent | |
| advance(self, float t, float thrust_N, float mdot_kg_s) | engine.layerx.flight.InlineAscent | |
| drag | engine.layerx.flight.InlineAscent | |
| dt_max | engine.layerx.flight.InlineAscent | |
| elevation | engine.layerx.flight.InlineAscent | |
| from_config(cls, Any config, float liftoff_mass_kg, float ambient_pa, *, Any drag=None, float dt_max=0.01) | engine.layerx.flight.InlineAscent | |
| held | engine.layerx.flight.InlineAscent | |
| held(self) | engine.layerx.flight.InlineAscent | |
| liftoff_time_s | engine.layerx.flight.InlineAscent | |
| m | engine.layerx.flight.InlineAscent | |
| mdot | engine.layerx.flight.InlineAscent | |
| p_ref | engine.layerx.flight.InlineAscent | |
| specific_force(self) | engine.layerx.flight.InlineAscent | |
| t | engine.layerx.flight.InlineAscent | |
| thrust | engine.layerx.flight.InlineAscent | |
| v | engine.layerx.flight.InlineAscent | |
| z | engine.layerx.flight.InlineAscent | |
1.15.0