Aerodynamics

This page provides a detailed description of the aerodynamics functions implemented in the HAOT package. For additional clarity, these descriptions can also be accessed and explored interactively in a Python session using the help() function.

haot.sutherland_law_viscosity(temperature_K, molecule='Air')[source]

Calculates the Sutherland’s law of viscosity

Parameters:

  • temperature_K (float) – reference temperature in [K]

  • molecule (str) – Air (default), Argon, N2, O2

Return type:

float

Returns:

dynamic viscosity in [kg/ms]

Examples

>> sutherland_law_viscosity(300.0)

Reference:

Viscous Fluid Flow, International Edition, 4th (White F., ISBN 978 1 260 59786)

haot.sutherland_law_conductivity(temperature_K, molecule='Air')[source]

Calculates the Sutherland’s law of thermal conductivity

Parameters:

  • temperature_K (float) – reference temperature in [K]

  • molecule (str) – Air (default), Argon, N2, O2

Return type:

float

Returns:

thermal conductivity in [W/mK]

Examples

>> sutherland_law_conductivity(300.0)

Reference:

Viscous Fluid Flow, International Edition, 4th (White F., ISBN 978 1 260 59786)

haot.air_atomic_molar_mass(molecules=None)[source]

Returns the atomic molar mass

Parameters:

molecule – Molecules that need the molar mass (11 species air is the default)

Return type:

dict[str, float]

Returns:

species in [g/mol]

Examples

>> air_atomic_molar_mass([“N+”, “N2”])

haot.speed_of_sound(temperature_K, adiabatic_indx=1.4)[source]

Calculates the speed of sound

Parameters:

  • temperature_K (float) – reference temperature in [K]

  • adiabatic_indx (float) – adiabatic index, 1.4 (default)

Return type:

float

Returns:

speed of sound in [m/s]

Examples

>> speed_of_sound(300.0)

haot.isentropic_relations(mach_1, adiabatic_indx=1.4)[source]

Calculates isentropic relations

Parameters:

mach_1 (float) – pre-shock mach number

Returns:

A dictionary containing:

  • pressure_s: pressure ratio (post-shock stagnation / pre-shock)

  • temperature_s: temperature ratio (post-shock stagnation / pre-shock)

  • density_s: density ratio (post-shock stagnation / pre-shock)

Return type:

dict

Examples

>> isentropic_relations(3.0)

Reference:

Modern Compressible Flow With Historic Perspective, International Edition 4th (Anderson J., ISBN 978 1 260 57082 3)

haot.normal_shock_relations(mach_1, adiabatic_indx=1.4)[source]

Calculates normal shock relations

Parameters:

  • mach_1 (float) – pre-shock mach number

  • adiabatic_indx (float) – adiabatic index, 1.4 (default)

Returns:

A dictionary containing:

  • mach_2: post-shock mach number

  • pressure_r: pressure ratio (post-shock / pre-shock)

  • temperature_r: temperature ratio (post-shock / pre-shock)

  • density_r: density ratio (post-shock / pre-shock)

  • pressure_s: stagnation pressure ratio (post-shock / pre-shock)

Return type:

dict

Reference:

Normal Shock Wave - NASA (https://www.grc.nasa.gov/www/k-12/airplane/normal.html)

haot.oblique_shock_angle(mach_1, deflection_angle_deg, adiabatic_indx=1.4)[source]

Calculates oblique shock angle for weak shocks and strong shocks

Parameters:

  • mach_1 (float) – pre-shock mach number

  • deflection_angle_deg (float) – deflection angle in degrees

  • adiabatic_indx (float) – adiabatic index, 1.4 (default)

Return type:

tuple[float, float]

Returns:

oblique shock angle in [degs]

Examples

>> oblique_shock_angle(3.0, 45.0)

Reference:

Modern Compressible Flow With Historic Perspective, International Edition 4th (Anderson J., ISBN 978 1 260 57082 3)

haot.oblique_shock_relations(mach_1, shock_angle_deg, adiabatic_indx=1.4)[source]

Calculates oblique shock relations for weak shocks

Parameters:

  • mach_1 (float) – pre-shock mach number

  • shock_angle_deg (float) – shock angle in degrees

  • adiabatic_indx (float) – adiabatic index, 1.4 (default)

Returns:

A dictionary containing:

  • mach_2: post-shock mach number

  • pressure_r: pressure ratio (post-shock / pre-shock)

  • temperature_r: temperature ratio (post-shock / pre-shock)

  • density_r: density ratio (post-shock / pre-shock)

  • deflection_angle_degs: deflection angle in [degs]

  • mach_n1: normal pre-shock mach number

  • mach_n2: normal post-shock mach number

Return type:

dict

Examples

>> oblique_shock_relations(3.0, 45.0)

Reference:

Modern Compressible Flow With Historic Perspective, International Edition 4th (Anderson J., ISBN 978 1 260 57082 3)