1113da21abe9b06a0a3251dcb6907d756073652e,trunk/SUAVE/Methods/Aerodynamics/AVL/AVL_Callable.py,,write_run_cases,#,188

Before Change

    // unpack avl_inputs
    files_path = self.settings.filenames.run_folder
    batch_path = os.path.abspath(os.path.join(files_path,self.settings.filenames.batches[-1]))
    aircraft   = self.features

    base_case_text = \
"""

 ---------------------------------------------
 Run case  {0}:   {1}

 alpha        ->  alpha       =   {2}
 beta         ->  beta        =   {3}
 pb/2V        ->  pb/2V       =   0.00000
 qc/2V        ->  qc/2V       =   0.00000
 rb/2V        ->  rb/2V       =   0.00000
{4}

 alpha     =   0.00000     deg
 beta      =   0.00000     deg
 pb/2V     =   0.00000
 qc/2V     =   0.00000
 rb/2V     =   0.00000
 CL        =  0.000000
 CDo       =  {5}
 bank      =   0.00000     deg
 elevation =   0.00000     deg
 heading   =   0.00000     deg
 Mach      =   {6}
 velocity  =   {7}     m/s
 density   =   {8}     kg/m^3
 grav.acc. =   {9}     m/s^2
 turn_rad. =   0.00000     m
 load_fac. =   0.00000
 X_cg      =   {10}     m
 Y_cg      =   {11}     m
 Z_cg      =   {12}     m
 mass      =   {13}     kg
 Ixx       =   {14}     kg-m^2
 Iyy       =   {15}     kg-m^2
 Izz       =   {16}     kg-m^2
 Ixy       =   {17}     kg-m^2
 Iyz       =   {18}     kg-m^2
 Izx       =   {19}     kg-m^2
 visc CL_a =   0.00000
 visc CL_u =   0.00000
 visc CM_a =   0.00000
 visc CM_u =   0.00000

"""//{4} is a set of control surface inputs that will vary depending on the control surface configuration


    // Open the geometry file after purging if it already exists
    purge_files([batch_path])
    runcases = open(batch_path,"w")

    try:
        x_cg = self.features.mass_properties.center_of_gravity[0]
        y_cg = self.features.mass_properties.center_of_gravity[1]

After Change

    // Open the geometry file after purging if it already exists
    purge_files([batch_filename])
    with open(batch_filename,"w") as runcases:

        x_cg = self.features.mass_properties.center_of_gravity[0]
        y_cg = self.features.mass_properties.center_of_gravity[1]
        z_cg = self.features.mass_properties.center_of_gravity[2]
        mass = 0 //self.default_case.mass TODO: FIGURE OUT WHAT TO DEFAULT MASS TO, AND WHERE TO STORE IT BEFORE ANALYSIS.
        moments_of_inertia = aircraft.mass_properties.moments_of_inertia.tensor
        Ixx  = moments_of_inertia[0][0]
        Iyy  = moments_of_inertia[1][1]
        Izz  = moments_of_inertia[2][2]
        Ixy  = moments_of_inertia[0][1]
        Iyz  = moments_of_inertia[1][2]
        Izx  = moments_of_inertia[2][0]

        for case in self.analysis_temps.current_cases:
            index = case.index
            name  = case.tag
            alpha = case.conditions.aerodynamics.angle_of_attack
            beta  = case.conditions.aerodynamics.side_slip_angle
            CD0   = case.conditions.aerodynamics.parasite_drag
            mach  = case.conditions.freestream.mach
            v     = case.conditions.freestream.velocity
            rho   = case.conditions.freestream.density
            g     = case.conditions.freestream.gravitational_acceleration

            // form controls text
            controls = []
            for cs in case.stability_and_control.control_deflections:
                cs_text = make_controls_case_text(cs)
                controls.append(cs_text)
            controls_text = "".join(controls)
            case_text = base_case_text.format(index,name,alpha,beta,controls_text,
                                              CD0,mach,v,rho,g,x_cg,y_cg,z_cg,mass,
                                              Ixx,Iyy,Izz,Ixy,Iyz,Izx)
            runcases.write(case_text)

    return


def write_input_deck(self):

Instances