.. DO NOT EDIT.
.. THIS FILE WAS AUTOMATICALLY GENERATED BY SPHINX-GALLERY.
.. TO MAKE CHANGES, EDIT THE SOURCE PYTHON FILE:
.. "auto_examples/optimum_speed_altitude.py"
.. LINE NUMBERS ARE GIVEN BELOW.

.. only:: html

    .. note::
        :class: sphx-glr-download-link-note

        :ref:`Go to the end <sphx_glr_download_auto_examples_optimum_speed_altitude.py>`
        to download the full example code.

.. rst-class:: sphx-glr-example-title

.. _sphx_glr_auto_examples_optimum_speed_altitude.py:


Optimisation Calculation
========================

Example of BADA4 and BADAH optimum speed and altitude calculation

.. GENERATED FROM PYTHON SOURCE LINES 7-115




.. rst-class:: sphx-glr-script-out

 .. code-block:: none

    BADA4 Optimum Speed and Altitude:
    EconMach =  0.786
    EconMach_precomputed =  0.7864553781649994
    MRC =  0.715
    MRC_precomputed =  0.7148916115931497
    LRC =  0.748
    LRC_precomputed =  0.7483447003614483
    MEC =  0.605
    MEC_precomputed =  0.6046258001683559
    optAlt = 36417.322834646
    optAlt_precomputed =  36358.049180327864

    BADAH Optimum Speed and Altitude:
    MRC =  67.4
    MRC_precomputed =  67.4006818433
    LRC =  67.4
    LRC_precomputed =  67.4006818433
    MEC =  32.29
    MEC_precomputed =  32.290089681






|

.. code-block:: Python


    from pyBADA import atmosphere as atm
    from pyBADA import conversions as conv

    from pyBADA.bada4 import Bada4Aircraft
    from pyBADA.badaH import BadaHAircraft

    badaVersion = "DUMMY"

    # initialization of BADA4
    AC = Bada4Aircraft(badaVersion=badaVersion, acName="Dummy-TWIN")
    print("BADA4 Optimum Speed and Altitude:")

    # BADA4
    if AC.BADAFamily.BADA4:
        mass = AC.MTOW  # [kg] AC weight
        h = conv.ft2m(33000)  # [m] AC flight altitdue
        DeltaTemp = 0  # [K] temperature deviation from ISA
        cI = 50  # [kg min^-1] cost index
        wS = 0  # [m s^-1] longitudinal wind speed

        [theta, delta, sigma] = atm.atmosphereProperties(
            h=h, DeltaTemp=DeltaTemp
        )  # atmosphere properties

        # Economic Mach Cruise Speed
        econMach = AC.OPT.econMach(
            theta=theta, delta=delta, mass=mass, DeltaTemp=DeltaTemp, cI=cI, wS=wS
        )
        print("EconMach = ", econMach)

        CCI = AC.OPT.CCI(theta=theta, delta=delta, cI=cI)
        CW = AC.OPT.CW(mass=mass, delta=delta)
        econMach_precomputed = AC.OPT.getOPTParam("ECON", CW, CCI)
        print("EconMach_precomputed = ", econMach_precomputed)

        # Maximum Range Cruise (MRC) Mach speed
        MRC = AC.OPT.MRC(
            theta=theta, delta=delta, mass=mass, DeltaTemp=DeltaTemp, wS=wS
        )
        print("MRC = ", MRC)

        MRC_precomputed = AC.OPT.getOPTParam("MRC", CW)
        print("MRC_precomputed = ", MRC_precomputed)

        # Long Range Cruise (LRC) Mach speed
        LRC = AC.OPT.LRC(
            theta=theta, delta=delta, mass=mass, DeltaTemp=DeltaTemp, wS=wS
        )
        print("LRC = ", LRC)

        LRC_precomputed = AC.OPT.getOPTParam("LRC", CW)
        print("LRC_precomputed = ", LRC_precomputed)

        # Maximum Endurance Cruise (MEC) Mach speed
        MEC = AC.OPT.MEC(
            theta=theta, delta=delta, mass=mass, DeltaTemp=DeltaTemp, wS=wS
        )
        print("MEC = ", MEC)

        MEC_precomputed = AC.OPT.getOPTParam("MEC", CW)
        print("MEC_precomputed = ", MEC_precomputed)

        # optimum flight altitude at given M speed
        M = MRC
        optAlt = AC.OPT.optAltitude(M=M, mass=mass, DeltaTemp=DeltaTemp)
        print("optAlt =", optAlt)

        optAlt_precomputed = AC.OPT.getOPTParam("OPTALT", M, mass)
        print("optAlt_precomputed = ", optAlt_precomputed)

    # initialization of BADAH
    AC = BadaHAircraft(badaVersion=badaVersion, acName="DUMH")
    print("\nBADAH Optimum Speed and Altitude:")

    # BADAH
    if AC.BADAFamily.BADAH:
        mass = 1600  # [kg] AC weight
        Hp = 14000  # [ft] AC flight altitude
        h = conv.ft2m(Hp)  # [m] AC flight altitude
        DeltaTemp = 20  # [K] temperature deviation from ISA
        wS = 0  # [m s^-1] longitudinal wind speed

        [theta, delta, sigma] = atm.atmosphereProperties(
            h=h, DeltaTemp=DeltaTemp
        )  # atmoshpere properties

        # Maximum Range Cruise (MRC) Mach speed
        MRC = AC.OPT.MRC(h=h, mass=mass, DeltaTemp=DeltaTemp, wS=wS)
        # print("MRC = ", conv.ms2kt(MRC))
        print("MRC = ", (MRC))

        MRC_precomputed = AC.OPT.getOPTParam("MRC", Hp, mass, DeltaTemp)
        print("MRC_precomputed = ", conv.kt2ms(MRC_precomputed))

        # Long Range Cruise (LRC) Mach speed
        LRC = AC.OPT.LRC(h=h, mass=mass, DeltaTemp=DeltaTemp, wS=wS)
        print("LRC = ", (LRC))

        LRC_precomputed = AC.OPT.getOPTParam("LRC", Hp, mass, DeltaTemp)
        print("LRC_precomputed = ", conv.kt2ms(LRC_precomputed))

        # Maximum Endurance Cruise (MEC) Mach speed
        MEC = AC.OPT.MEC(h=h, mass=mass, DeltaTemp=DeltaTemp, wS=wS)
        print("MEC = ", (MEC))

        MEC_precomputed = AC.OPT.getOPTParam("MEC", Hp, mass, DeltaTemp)
        print("MEC_precomputed = ", conv.kt2ms(MEC_precomputed))


.. rst-class:: sphx-glr-timing

   **Total running time of the script:** (0 minutes 0.278 seconds)


.. _sphx_glr_download_auto_examples_optimum_speed_altitude.py:

.. only:: html

  .. container:: sphx-glr-footer sphx-glr-footer-example

    .. container:: sphx-glr-download sphx-glr-download-jupyter

      :download:`Download Jupyter notebook: optimum_speed_altitude.ipynb <optimum_speed_altitude.ipynb>`

    .. container:: sphx-glr-download sphx-glr-download-python

      :download:`Download Python source code: optimum_speed_altitude.py <optimum_speed_altitude.py>`

    .. container:: sphx-glr-download sphx-glr-download-zip

      :download:`Download zipped: optimum_speed_altitude.zip <optimum_speed_altitude.zip>`


.. only:: html

 .. rst-class:: sphx-glr-signature

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