Aerodynamics

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

Calculates the Sutherland’s law of viscosity

Parameters:
  • temperature_K (float) – reference temperature

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

Returns:

[kg/ms]

Return type:

dynamic_viscosity (float)

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

Calculates the Sutherland’s law of thermal conductivity

Parameters:
  • temperature_K (float) – reference temperature

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

Returns:

[W/mK]

Return type:

thermal_conductivity (float)

haot.air_atomic_molar_mass()[source]

Returns the atomic molar mass of an 11-species air in [g/mol]

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

Calculates the speed of sound

Parameters:
  • temperature_K (float) – reference temperature

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

Returns:

speed of sound in [m/s]

Return type:

spd_of_sound (float)

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

Calculates normal shock relations

Reference:

https://www.grc.nasa.gov/www/k-12/airplane/normal.html

Parameters:
  • mach_1 (float) – pre-shock mach number

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

Returns:

dictionary with normal shock properties

mach_2 (float): post-shock mach number [ ] pressure_r (float): pressure ratio (post-shock / pre-shock) [ ] temperature_r (float): temperature ratio (post-shock / pre-shock) [ ] density_r (float): density ratio (post-shock / pre-shock) [ ] pressure_tr (float): stagnation pressure ratio (post-shock / pre-shock) [ ] temperature_tr (float): stagnation temperature ratio (post-shock / pre-shock) [ ]

Return type:

normal_shock_dic

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