vehicle_drag.py File Reference

Go to the source code of this file.

Classes
class	engine.pipeline.vehicle_drag.VehicleGeometry
class	engine.pipeline.vehicle_drag.DragCurves

Namespaces
namespace	engine
namespace	engine.pipeline
namespace	engine.pipeline.vehicle_drag

Functions
Tuple[float, float, float, float, float]	engine.pipeline.vehicle_drag.isa_troposphere (float h_m)
float	engine.pipeline.vehicle_drag.skin_friction_cf (float Re, float mach, float roughness_m, float length_m)
float	engine.pipeline.vehicle_drag.stagnation_cd (float mach)
float	engine.pipeline.vehicle_drag.base_cd (float mach)
float	engine.pipeline.vehicle_drag._subsonic_fit (float M, float m_lo, float value, float slope, float cd0)
str	engine.pipeline.vehicle_drag._nose_key (str kind)
float	engine.pipeline.vehicle_drag._haack_wave_cd (float mach, float fineness, str key)
float	engine.pipeline.vehicle_drag._cone_wave_cd (float mach, float fineness, float cd0, float shape_factor)
float	engine.pipeline.vehicle_drag.nose_pressure_cd (float mach, str kind, float fineness)
float	engine.pipeline.vehicle_drag.fin_pressure_cd (float mach, str profile, float le_sweep_rad)
np.ndarray	engine.pipeline.vehicle_drag.nose_profile (str kind, float length_m, float radius_m, np.ndarray x)
float	engine.pipeline.vehicle_drag.nose_wetted_area (str kind, float length_m, float radius_m, int n=20001)
float	engine.pipeline.vehicle_drag._tank_height (Any section, str h_attr, str r_attr)
Dict[str, float]	engine.pipeline.vehicle_drag.built_stack (Any config)
VehicleGeometry	engine.pipeline.vehicle_drag.vehicle_geometry (Any config, float nozzle_exit_area_m2, Optional[Dict[str, float]] stack=None)
Dict[str, float]	engine.pipeline.vehicle_drag.drag_components (VehicleGeometry geom, float mach, *, float a_m_s, float nu_m2_s, bool thrusting)
DragCurves	engine.pipeline.vehicle_drag.buildup_curves (VehicleGeometry geom, float reference_altitude_m, Sequence[float] mach_grid=MACH_GRID)
DragCurves	engine.pipeline.vehicle_drag.table_curves (Sequence[Sequence[float]] power_off, Sequence[Sequence[float]] power_on, str source)
DragCurves	engine.pipeline.vehicle_drag.resolve_drag_curves (Any config, float nozzle_exit_area_m2, Optional[Dict[str, float]] stack=None, **Any overrides)

Variables
float	engine.pipeline.vehicle_drag.GAMMA_AIR = 1.4
float	engine.pipeline.vehicle_drag.R_AIR = 287.05287
tuple	engine.pipeline.vehicle_drag.FIN_PROFILES = ("square", "rounded", "airfoil")
str	engine.pipeline.vehicle_drag.MODEL_NAME = "openrocket_barrowman"
	engine.pipeline.vehicle_drag.MACH_GRID = tuple(round(0.01 * i, 2) for i in range(1, 201))
dict	engine.pipeline.vehicle_drag._STONEY_FN3