flightcondition 22.8.10

Install Commands

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

pip install flightcondition

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

pip install <path/to/flightcondition>

Dependencies

• numpy: package for scientific computing.

• pint: package for dealing with units.

Flight Condition

The FlightCondition class is used to compute and interact with common flight condition data. Inputs include altitude, airspeed in some format, and an optional length scale.

Input arguments include:

1. h geometric altitude - aliases are alt, altitude

2. Velocity (pick one):

   • TAS true airspeed - aliases are tas, true_airspeed, U_inf, V_inf

   • CAS calibrated airspeed - aliases are cas, calibrated_airspeed

   • EAS equivalent airspeed - aliases are eas, equivalent_airspeed

   • M mach number - aliases are mach, Mach, M_inf, mach_number

3. L length scale (optional) - aliases are ell, len, length, length_scale, l

See also the KTAS, KCAS, and KEAS syntactic sugar. For example, KCAS=233 is equivalent to CAS=233*unit('knots').

Outputs include:

1. atm atmospheric quantities - see Atmosphere class below.

2. vel airspeed quantities:

   • True airspeed TAS

   • Calibrated airspeed CAS

   • Equivalent airspeed EAS

   • Mach number M

   • Dynamic pressure q_inf

   • Impact pressure q_c

   • Stagnation pressure p_0

   • Stagnation temperature T_0

   • Reynolds number per unit length Re_by_L

3. len length-scale quantities:

   • Reynolds number Re

Quantities may be accessed using the specific atm, vel, or len object. Quantities may also be accessed using their full name with the byname object. For example, Mach number can be accessed using .vel.M or by its full name using .byname.mach_number

Example usage:

from flightcondition import FlightCondition, unit, dimless

# Compute flight condition at 3 km, Mach 0.5
fc = FlightCondition(3*unit('km'), M=0.5)

# Uncomment to print summary of flight condition quantities:
#print(f"{fc}")

# Uncomment to print abbreviated output in US units:
#print(f"\n{fc.tostring(full_output=False, unit_system="US")}")

# Access true, calibrated, equivalent airspeeds
KTAS = fc.vel.TAS.to('knots')
KCAS = fc.vel.CAS.to('knots')
KEAS = fc.vel.EAS.to('knots')
print(f"Flying at {KTAS.magnitude:.4g} KTAS,"
    f" which is {KCAS.magnitude:.4g} KCAS,"
    f" or {KEAS.magnitude:.4g} KEAS")
# >>> Flying at 319.4 KTAS, which is 277.7 KCAS, or 275.1 KEAS

# Access atmospheric data (see Atmosphere class for more)
atm = fc.atm  # access Atmosphere object
h, p, T, rho, nu, a = atm.h, atm.p, atm.T, atm.rho, atm.nu, atm.a
print(f"The ambient temperature at {h.to('km'):.4g} is {T:.4g}")
# >>> The ambient temperature at 3 km is 268.7 K

# Compute again instead using true airspeed and altitude in km
fc = FlightCondition(3.048*unit('km'), TAS=401.7*unit('mph'))
#print(f"{fc}")  # uncomment to print output

# Compute for a range of altitudes at 275.14 knots-equivalent
# airspeed with a characteristic length scale of 10 meters
fc = FlightCondition([0, 9.8425, 20]*unit('kft'),
                    EAS=275.14*unit('kt'),
                    L=10*unit('m'))

# Compute additional derived quantities
# Explore the class data structure for all options
print(f"\nThe dynamic pressure in psi is "
    f"{fc.vel.q_inf.to('psi'):.3g}")
# >>> The dynamic pressure in psi is [1.78 1.78 1.78] psi
print(f"The Reynolds number is {fc.len.Re:.3g}")
# >>> The Reynolds number is [9.69e+07 8.82e+07 7.95e+07]

# Alternatively access quantities by their full name
print(fc.vel.TAS == fc.byname.true_airspeed)
# >>> [ True  True  True]

Atmosphere

The Atmosphere class 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 MFP

Usage:

from flightcondition import Atmosphere, unit

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

# Uncomment to print all atmospheric quantities:
#print(f"\n{atm}")

# Uncomment to print while specifying abbreviated output in US units:
#print(f"\n{atm.tostring(full_output=False, unit_system="US")}")

# 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, k = atm.p, atm.T, atm.rho, atm.nu, atm.a, atm.k
print(f"\nThe pressure in psi is {p.to('psi'):.3g}")
# >>> The pressure in psi is [14.7 0.024 0.000129] psi

# Compute additional properties such as mean free path
# Explore the class data structure for all options
print( f"\nThe mean free path = {atm.MFP:.3g}")
# >>> The mean free path = [7.25e-08 4.04e-05 0.00564] yd

Units

Conveniently input, output, and convert units using pint units.

from flightcondition import unit, printv

h = 33 * unit('km')
print(h.to('kft'))
# >>> 108.26771653543307 kft
printv(h, to='kft')
# >>> h = 108.27 kft

U_inf = 20 * unit('knots')
rho_inf = 1.225 * unit('kg/m^3')
q_inf = 0.5*rho_inf*U_inf**2
printv(q_inf, to='psi')
# >>> q_inf = 0.0094042 psi

Note that pint does not support conflicting unit registries so avoid interactions between flightcondition.unit and a separate pint.UnitRegistry.

Command Line Interface

A command line interface (CLI) is included for convenience but with limited functionality. Run flightcondition -h for help.

An example call is given for the flight condition of 233 knots-equivalent-airspeed at 23 kilofeet with a length scale of 4 feet and abbreviated output:

flightcondition --alt 23 kft --EAS 233 knots --len 4 ft --abbreviated

=========================================================
    Flight Condition (US units, abbreviated output)
=========================================================
-----------------  Altitude Quantities  -----------------
geometric_altitude    h       = 23 kft
pressure              p       = 857.25 lbf/ft²
temperature           T       = 436.74 °R
density               rho     = 1.1435×10⁻³ slug/ft³
sound_speed           a       = 1024.5 ft/s
kinematic_viscosity   nu      = 2.8509×10⁻⁴ ft²/s
-----------------  Velocity Quantities  -----------------
true_airspeed         TAS     = 566.99 ft/s
calibrated_airspeed   CAS     = 401.94 ft/s
equivalent_airspeed   EAS     = 393.26 ft/s
mach_number           M       = 0.55344
reynolds_per_length   Re_by_L = 1.6573×10⁵ 1/in
-----------------   Length Quantities   -----------------
length_scale          L       = 4 ft
reynolds_number       Re      = 7.9551×10⁶

Alternatively use the --KEAS 233 syntactic sugar to omit the knots unit. See also --KTAS and --KCAS.