This repository contains all OpenAP databases and a Python toolkit that facilitates data access and performance computation.
OpenAP is a project actively maintained by Junzi Sun from TU Delft.
It is the continuation of his PhD thesis work (between 2015 and 2019). You can read more about OpenAP in this article.
Use the discussion board to give your feedback/suggestions, and use issue board to report bugs.
To install latest version of OpenAP from the GitHub:
pip install --upgrade git+https://github.com/junzis/openap- Aircraft
- Engines
- Drag polar
- Kinematic (WRAP model)
- Navigation
prop: aircraft and engine propertiesthrust: model to compute aircraft thrustdrag: model to compute aircraft dragfuel: model to compute fuel consumptionkinematic: a utility library to access WRAP dataaero: common aeronautical conversionsnav: model to access navigation informationsegment: a utility library to determine climb, cruise, descent, level flightphase: a wrapper aroundsegment, providing identification of all flight phasestraj: package contains a set of tools related with trajectory generation
from openap import prop
aircraft = prop.aircraft('A320')
engine = prop.engine('CFM56-5B4')from openap import Thrust
thrust = Thrust(ac='A320', eng='CFM56-5B4')
T = thrust.takeoff(tas=100, alt=0)
T = thrust.climb(tas=200, alt=20000, roc=1000)
T = thrust.cruise(tas=230, alt=32000)from openap import Drag
drag = Drag(ac='A320')
D = drag.clean(mass=60000, tas=200, alt=20000, path_angle=5)
D = drag.nonclean(mass=60000, tas=150, alt=100, flap_angle=20,
path_angle=10, landing_gear=True)from openap import FuelFlow
fuelflow = FuelFlow(ac='A320', eng='CFM56-5B4')
FF = fuelflow.at_thrust(acthr=50000, alt=30000)
FF = fuelflow.takeoff(tas=100, alt=0, throttle=1)
FF = fuelflow.enroute(mass=60000, tas=200, alt=20000, path_angle=3)
FF = fuelflow.enroute(mass=60000, tas=230, alt=32000, path_angle=0)from openap import FuelFlow, Emission
fuelflow = FuelFlow(ac='A320', eng='CFM56-5B4')
emission = Emission(ac='A320', eng='CFM56-5B4')
TAS = 350
ALT = 30000
fuelflow = fuelflow.enroute(mass=60000, tas=TAS, alt=ALT) # kg/s
CO2 = emission.co2(fuelflow) # g/s
H2O = emission.h2o(fuelflow) # g/s
NOx = emission.nox(fuelflow, tas=TAS, alt=ALT) # g/s
CO = emission.co(fuelflow, tas=TAS, alt=ALT) # g/s
HC = emission.hc(fuelflow, tas=TAS, alt=ALT) # g/sfrom openap import WRAP
wrap = WRAP(ac='A320')
param = wrap.takeoff_speed()
param = wrap.takeoff_distance()
param = wrap.takeoff_acceleration()
param = wrap.initclimb_vcas()
param = wrap.initclimb_vs()
param = wrap.climb_range()
param = wrap.climb_const_vcas()
param = wrap.climb_const_mach()
param = wrap.climb_cross_alt_concas()
param = wrap.climb_cross_alt_conmach()
param = wrap.climb_vs_pre_concas()
param = wrap.climb_vs_concas()
param = wrap.climb_vs_conmach()
param = wrap.cruise_range()
param = wrap.cruise_alt()
param = wrap.cruise_init_alt()
param = wrap.cruise_mach()
param = wrap.descent_range()
param = wrap.descent_const_mach()
param = wrap.descent_const_vcas()
param = wrap.descent_cross_alt_conmach()
param = wrap.descent_cross_alt_concas()
param = wrap.descent_vs_conmach()
param = wrap.descent_vs_concas()
param = wrap.descent_vs_post_concas()
param = wrap.finalapp_vcas()
param = wrap.finalapp_vs()
param = wrap.landing_speed()
param = wrap.landing_distance()
param = wrap.landing_acceleration()from openap.traj import Generator
trajgen = Generator(ac='a320')
trajgen.enable_noise() # enable Gaussian noise in trajectory data
data_cl = trajgen.climb(dt=10, random=True) # using random paramerters
data_cl = trajgen.climb(dt=10, cas_const_cl=280, mach_const_cl=0.78, alt_cr=35000)
data_de = trajgen.descent(dt=10, random=True)
data_de = trajgen.descent(dt=10, cas_const_de=280, mach_const_de=0.78, alt_cr=35000)
data_cr = trajgen.cruise(dt=60, random=True)
data_cr = trajgen.cruise(dt=60, range_cr=2000, alt_cr=35000, m_cr=0.78)
data_all = trajgen.complete(dt=10, random=True)
data_all = trajgen.complete(dt=10, alt_cr=35000, m_cr=0.78,
cas_const_cl=260, cas_const_de=260)import pandas as pd
from openap import FlightPhase
df = pd.read_csv('data/trajectory.csv')
ts = df['ts'].values # timestamp, int, second
alt = df['alt'].values # altitude, int, ft
spd = df['spd'].values # speed, int, kts
roc = df['roc'].values # vertical rate, int, ft/min
fp = FlightPhase()
fp.set_trajectory(ts, alt, spd, roc)
labels = fp.phaselabel()@article{sun2020openap,
title={OpenAP: An open-source aircraft performance model for air transportation studies and simulations},
author={Sun, Junzi and Hoekstra, Jacco M and Ellerbroek, Joost},
journal={Aerospace},
volume={7},
number={8},
pages={104},
year={2020},
publisher={Multidisciplinary Digital Publishing Institute}
}