Expand description
§Compressible Flow
comp-flow is a collection of functions for basic compressible flow relations.
The included functions have no input checking or error handling whatsoever. Invalid (non-physical) inputs such as mach < 1 for a shock relation or gamma < 1 may produce non-sensical outputs.
Modules§
- der_
mach_ to - Derivatives of relations as a function of Mach number
- der_
normal - mach_
from - Collection of functions for isentropic compressible flow. TODO: finish documentation
- mach_to
- Collection of functions for isentropic compressible flow.
- normal
- Normal Shock relations
- oblique
- Weak oblique shock functions
Functions§
- der_
mach_ to_ a_ ac - der_
mach_ to_ f_ mcpt0 - der_
mach_ to_ mcpt0_ ap - der_
mach_ to_ mcpt0_ ap0 - der_
mach_ to_ p0_ p - der_
mach_ to_ rho0_ rho - der_
mach_ to_ t0_ t - Total temperature ratio for given mach number and specific heat ratio
- der_
mach_ to_ v_ cpt0 - der_
normal_ mach2 - der_
normal_ p02_ p01 - mach_
from_ a_ ac - Mach number for a given critical area ratio.
- mach_
from_ f_ mcpt0 - mach_
from_ mach_ angle - Mach number for a given mach angle in radians.
- mach_
from_ mcpt0_ ap - mach_
from_ mcpt0_ ap0 - mach_
from_ normal_ mach2 - mach_
from_ normal_ p02_ p01 - mach_
from_ p0_ p - mach_
from_ p_ p0 - Mach number for a given total pressure ratio.
- mach_
from_ pm_ angle - Mach number for a given Prandtl-Meyer angle in radians.
- mach_
from_ rho0_ rho - mach_
from_ rho_ rho0 - Mach number for a given stagnation density ratio.
- mach_
from_ t0_ t - Mach number for a given total temperature ratio.
- mach_
from_ t_ t0 - Mach number for a given total temperature ratio.
- mach_
from_ v_ cpt0 - mach_
to_ a_ ac - Critical area ratio for given Mach number and specific heat ratio
- mach_
to_ f_ mcpt - Impulse function for given Mach number and specific heat ratio
- mach_
to_ mach_ angle - Mach angle in radians for a given mach number.
- mach_
to_ mcpt0_ ap - Static normalised mass flow for given Mach number and specific heat ratio
- mach_
to_ mcpt0_ ap0 - Normalised mass flow for given Mach number and specific heat ratio
- mach_
to_ p0_ p - Total pressure ratio for given mach number and specific heat ratio
- mach_
to_ p_ p0 - Total pressure ratio for given mach number and specific heat ratio
- mach_
to_ pm_ angle - Prandtl-Meyer angle in radians for a given mach number and specific heat ratio.
- mach_
to_ rho0_ rho - Stagnation density ratio for given mach number and specific heat ratio
- mach_
to_ rho_ rho0 - Stagnation density ratio for given mach number and specific heat ratio
- mach_
to_ t0_ t - Total temperature ratio for given mach number and specific heat ratio
- mach_
to_ t_ t0 - Total temperature ratio for given mach number and specific heat ratio
- mach_
to_ v_ cpt0 - Normalised velocity for given Mach number and specific heat ratio
- normal_
a2_ a1 - Speed of sound ratio across normal shock
- normal_
mach2 - Mach number after normal shock
- normal_
p02_ p01 - Total pressure ratio across normal shock
- normal_
p2_ p1 - Static pressure ratio across normal shock
- normal_
rho2_ rho1 - Static density ratio across normal shock
- normal_
t2_ t1 - Static temperature ratio across normal shock
- oblique_
a2_ a1 - Speed of sound ratio across weak oblique shock
- oblique_
beta - Wave angle for weak oblique shock
- oblique_
beta_ max - Maximum oblique shock angle
- oblique_
mach2 - Mach number after weak oblique shock
- oblique_
p02_ p01 - Stagnation pressure ratio across weak oblique shock
- oblique_
p2_ p1 - Static pressure ratio across weak oblique shock
- oblique_
rho2_ rho1 - Static density ratio across weak oblique shock
- oblique_
t2_ t1 - Static temperature ratio across weak oblique shock