aeroutils 22.3

Importable utilities for aerospace problem solving.

About

This module contains commonly-used aerospace utilities for problem solving.

• Flight Condition: input altitude to compute common flight condition data. Easily swap between Mach number, true airspeed, calibrated airspeed, and equivalent airspeed. Includes atmospheric data.

• Atmosphere: input altitude to compute 1993 International Standard Atmosphere data. Many relevant, derived quantities are included.

Author

Matthew C. Jones <[e-mail]>

Installation

Install Commands

Install using the pip package-management system. The easiest method is to open the terminal and run:

pip install aeroutils

Alternatively, manually download the source code, unpack, and run:

pip install <path/to/aeroutils>

Dependencies

• numpy: widely-used package for scientific computing.

• pint: package for dealing with units.

Usage

In a Python script or an ipython notebook, import all utilities with:

from aeroutils import *

Flight Condition Package

The flightcondition package can be used to compute and interact with common flight condition data.

Outputs include:

• Mach number mach

• True airspeed TAS

• Calibrated airspeed CAS

• Equivalent airspeed EAS

• Dynamic pressure q_inf

• Reynolds number reynolds_number(ell)

• Reynolds number per-unit-length reynolds_number_per_unit_length(length_unit)

• Atmosphere data atm (see atmosphere below)

Usage:

from aeroutils import FlightCondition, unit, dimless

# Compute flight conditions for a scalar or array of altitudes
altitudes = [0, 10e3, 33.5e3] * unit('ft')
fc = FlightCondition(altitudes, EAS=300*unit('knots'))

# Print flight condition data:
print(f"{fc}")

# Print extended output in Imperial units:
print(f"\n{fc.tostring(full_output=True, imperial_units=True)}")

# Access flight speed formats individually
M_inf, U_inf, U_CAS, U_EAS = fc.mach, fc.TAS, fc.CAS, fc.EAS

# Access atmospheric data alone (see Atmosphere class for options)
atm = fc.atm  # access Atmosphere object 'atm'
p, T, rho, nu, a = atm.p, atm.T, atm.rho, atm.nu, atm.a

# Input true/calibrated/equivalent airspeed or Mach number
fc_TAS = FlightCondition(altitudes, TAS=300*unit('knots'))
fc_CAS = FlightCondition(altitudes, CAS=300*unit('knots'))
fc_EAS = FlightCondition(altitudes, EAS=300*unit('knots'))
fc_mach = FlightCondition(altitudes, mach=0.4535*dimless)

# Specify desired units on input and output
altitudes_in_km = [0, 3.048, 10.2108] * unit('km')
fc_other_units = FlightCondition(altitudes, EAS=154.33*unit('m/s'))
U_TAS = fc_other_units.TAS
print(f"\nThe true airspeed in m/s is {U_TAS.to('m/s'):.5g}")
print(f"The true airspeed in km/s is {U_TAS.to('km/s'):.5g}")

# Compute additional derived quantities (see class for all options)
print(f"\nThe dynamic pressure in psi is {fc.q_inf.to('psi'):.5g}")
ell = 60 * unit('in')  # arbitrary length scale of interest
print(f"The Reynolds number is {fc.reynolds_number(ell):.5g}")
print(f"The Reynolds number per-unit-length [1/in] is "
    f"{fc.reynolds_number_per_unit_length('in'):.5g}")

Atmosphere Package

The atmosphere package can be used to compute and interact with common standard atmosphere data and derived quantities.

Outputs include:

• Pressure p

• Temperature T

• Density rho

• Sound speed a

• Dynamic viscosity mu

• Kinematic viscosity nu

• Thermal conductivity k

• Layer name layer.name

• Geometric altitude h

• Geopotential altitude H

• Acceleration due to gravity g

• Mean free path mean_free_path

Usage:

from aeroutils import Atmosphere, unit

# Compute atmospheric data for a scalar or array of altitudes
h = [0.0, 12.7, 44.2, 81.0] * unit('km')
atm = Atmosphere(h)

# Print abbreviated output:
print(f"\n{atm}")

# Print extended output in Imperial units:
print(f"\n{atm.tostring(full_output=True, imperial_units=True)}")

# See also the linspace() function from numpy, e.g.
# h = linspace(0, 81.0, 82) * unit('km')

# Access individual properties and convert to desired units: "
p, T, rho, nu, a = atm.p, atm.T, atm.rho, atm.nu, atm.a
print(f"\nThe pressure in psi is {p.to('psi'):.5g}")

# Compute additional properties such as thermal conductivity,
# mean free path, and more (see class for all options)
print(f"\nThe thermal conductivity is {atm.k:.5g}"
    f"\nThe mean free path = {atm.mean_free_path:.5g}")

License

aeroutils is licensed under the MIT LICENSE. See the LICENSE document.

Disclaimer

The software is provided “as is”, without warranty of any kind, express or implied, including but not limited to the warranties of merchantability, fitness for a particular purpose and noninfringement. In no event shall the authors or copyright holders be liable for any claim, damages or other liability, whether in an action of contract, tort or otherwise, arising from, out of or in connection with the software or the use or other dealings in the software.