aerosandbox.library.aerodynamics.normal_shock_relations
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Module Contents#
Functions#
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Computes the mach number immediately after a normal shock wave. |
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Computes the ratio of fluid density across a normal shock. |
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Computes the ratio of fluid temperature across a normal shock. |
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Computes the ratio of fluid static pressure across a normal shock. |
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Computes the ratio of fluid total pressure across a normal shock. |
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- 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