`aerosandbox.atmosphere.thermodynamics.isentropic_flow`#

Module Contents#

`temperature_over_total_temperature`(mach[, gamma])	Gives T/T_t, the ratio of static temperature to total temperature.
`pressure_over_total_pressure`(mach[, gamma])	Gives P/P_t, the ratio of static pressure to total pressure.
`density_over_total_density`(mach[, gamma])	Gives rho/rho_t, the ratio of density to density after isentropic compression.
`area_over_choked_area`(mach[, gamma])	Gives A/A^* (where A^* is "A-star"), the ratio of cross-sectional flow area to the cross-sectional flow area that would result in choked (M=1) flow.

aerosandbox.atmosphere.thermodynamics.isentropic_flow.temperature_over_total_temperature(mach, gamma=1.4)[source]#

Gives T/T_t, the ratio of static temperature to total temperature.

Parameters:

mach – Mach number [-]
gamma – The ratio of specific heats. 1.4 for air across most temperature ranges of interest.

aerosandbox.atmosphere.thermodynamics.isentropic_flow.pressure_over_total_pressure(mach, gamma=1.4)[source]#

Gives P/P_t, the ratio of static pressure to total pressure.

Parameters:

mach – Mach number [-]
gamma – The ratio of specific heats. 1.4 for air across most temperature ranges of interest.

aerosandbox.atmosphere.thermodynamics.isentropic_flow.density_over_total_density(mach, gamma=1.4)[source]#

Gives rho/rho_t, the ratio of density to density after isentropic compression.

Parameters:

mach – Mach number [-]
gamma – The ratio of specific heats. 1.4 for air across most temperature ranges of interest.

aerosandbox.atmosphere.thermodynamics.isentropic_flow.area_over_choked_area(mach, gamma=1.4)[source]#

Gives A/A^* (where A^* is “A-star”), the ratio of cross-sectional flow area to the cross-sectional flow area that would result in choked (M=1) flow.

Applicable to 1D isentropic nozzle flow.

Parameters:

mach – Mach number [-]
gamma – The ratio of specific heats. 1.4 for air across most temperature ranges of interest.