<filename>openconcept/analysis/atmospherics/mach_number_comp.py
from __future__ import division
import numpy as np

from openmdao.api import ExplicitComponent

class MachNumberComp(ExplicitComponent):
    '''
    Computes mach number from true airspeed and speed of sound

    Inputs
    ------
    fltcond|a : float
        Speed of sound (vector, m/s)
    fltcond|Utrue : float
        True airspeed (vector, m/s)

    Outputs
    -------
    fltcond|M : float
        Mach number (vector, dimensionless)

    Options
    -------
    num_nodes : int
        Number of analysis points to run (sets vec length) (default 1)
    '''

    def initialize(self):
        self.options.declare('num_nodes', types=int)

    def setup(self):
        num_points = self.options['num_nodes']

        self.add_input('fltcond|a', units='m / s', shape=num_points)
        self.add_input('fltcond|Utrue', units='m /s', shape=num_points)
        self.add_output('fltcond|M', shape=num_points)

        arange = np.arange(num_points)
        self.declare_partials('fltcond|M', 'fltcond|a', rows=arange, cols=arange)
        self.declare_partials('fltcond|M', 'fltcond|Utrue', rows=arange, cols=arange)

    def compute(self, inputs, outputs):
        outputs['fltcond|M'] = inputs['fltcond|Utrue'] / inputs['fltcond|a']

    def compute_partials(self, inputs, partials):
        num_points = self.options['num_nodes']
        partials['fltcond|M', 'fltcond|Utrue'] = np.ones(num_points) / inputs['fltcond|a']
        partials['fltcond|M', 'fltcond|a'] = - inputs['fltcond|Utrue'] / (inputs['fltcond|a'] ** 2)
<filename>openconcept/analysis/atmospherics/mach_number_comp.py
from __future__ import division
import numpy as np

from openmdao.api import ExplicitComponent

class MachNumberComp(ExplicitComponent):
    '''
    Computes mach number from true airspeed and speed of sound

    Inputs
    ------
    fltcond|a : float
        Speed of sound (vector, m/s)
    fltcond|Utrue : float
        True airspeed (vector, m/s)

    Outputs
    -------
    fltcond|M : float
        Mach number (vector, dimensionless)

    Options
    -------
    num_nodes : int
        Number of analysis points to run (sets vec length) (default 1)
    '''

    def initialize(self):
        self.options.declare('num_nodes', types=int)

    def setup(self):
        num_points = self.options['num_nodes']

        self.add_input('fltcond|a', units='m / s', shape=num_points)
        self.add_input('fltcond|Utrue', units='m /s', shape=num_points)
        self.add_output('fltcond|M', shape=num_points)

        arange = np.arange(num_points)
        self.declare_partials('fltcond|M', 'fltcond|a', rows=arange, cols=arange)
        self.declare_partials('fltcond|M', 'fltcond|Utrue', rows=arange, cols=arange)

    def compute(self, inputs, outputs):
        outputs['fltcond|M'] = inputs['fltcond|Utrue'] / inputs['fltcond|a']

    def compute_partials(self, inputs, partials):
        num_points = self.options['num_nodes']
        partials['fltcond|M', 'fltcond|Utrue'] = np.ones(num_points) / inputs['fltcond|a']
        partials['fltcond|M', 'fltcond|a'] = - inputs['fltcond|Utrue'] / (inputs['fltcond|a'] ** 2)
Computes mach number from true airspeed and speed of sound      Inputs     ------     fltcond|a : float         Speed of sound (vector, m/s)     fltcond|Utrue : float         True airspeed (vector, m/s)      Outputs     -------     fltcond|M : float         Mach number (vector, dimensionless)      Options     -------     num_nodes : int         Number of analysis points to run (sets vec length) (default 1)