aerosandbox.library.aerodynamics.normal_shock_relations#

Module Contents#

Functions#

mach_number_after_normal_shock(mach_upstream[, gamma])

Computes the mach number immediately after a normal shock wave.

density_ratio_across_normal_shock(mach_upstream[, gamma])

Computes the ratio of fluid density across a normal shock.

temperature_ratio_across_normal_shock(mach_upstream[, ...])

Computes the ratio of fluid temperature across a normal shock.

pressure_ratio_across_normal_shock(mach_upstream[, gamma])

Computes the ratio of fluid static pressure across a normal shock.

total_pressure_ratio_across_normal_shock(mach_upstream)

Computes the ratio of fluid total pressure across a normal shock.

q_ratio(mach)

aerosandbox.library.aerodynamics.normal_shock_relations.mach_number_after_normal_shock(mach_upstream, gamma=1.4)[source]#

Computes the mach number immediately after a normal shock wave.

Parameters:

  • mach_upstream – The mach number immediately before the normal shock wave.

  • gamma – The ratio of specific heats of the fluid. 1.4 for air.

Returns: The mach number immediately after the normal shock wave.

aerosandbox.library.aerodynamics.normal_shock_relations.density_ratio_across_normal_shock(mach_upstream, gamma=1.4)[source]#

Computes the ratio of fluid density across a normal shock.

Specifically, returns: rho_after_shock / rho_before_shock

Parameters:

  • mach_upstream – The mach number immediately before the normal shock wave.

  • gamma – The ratio of specific heats of the fluid. 1.4 for air.

Returns: rho_after_shock / rho_before_shock

aerosandbox.library.aerodynamics.normal_shock_relations.temperature_ratio_across_normal_shock(mach_upstream, gamma=1.4)[source]#

Computes the ratio of fluid temperature across a normal shock.

Specifically, returns: T_after_shock / T_before_shock

Parameters:

  • mach_upstream – The mach number immediately before the normal shock wave.

  • gamma – The ratio of specific heats of the fluid. 1.4 for air.

Returns: T_after_shock / T_before_shock

aerosandbox.library.aerodynamics.normal_shock_relations.pressure_ratio_across_normal_shock(mach_upstream, gamma=1.4)[source]#

Computes the ratio of fluid static pressure across a normal shock.

Specifically, returns: P_after_shock / P_before_shock

Parameters:

  • mach_upstream – The mach number immediately before the normal shock wave.

  • gamma – The ratio of specific heats of the fluid. 1.4 for air.

Returns: P_after_shock / P_before_shock

aerosandbox.library.aerodynamics.normal_shock_relations.total_pressure_ratio_across_normal_shock(mach_upstream, gamma=1.4)[source]#

Computes the ratio of fluid total pressure across a normal shock.

Specifically, returns: Pt_after_shock / Pt_before_shock

Parameters:

  • mach_upstream – The mach number immediately before the normal shock wave.

  • gamma – The ratio of specific heats of the fluid. 1.4 for air.

Returns: Pt_after_shock / Pt_before_shock

aerosandbox.library.aerodynamics.normal_shock_relations.q_ratio(mach)[source]#