SUAVE.Methods.Aerodynamics.AVL.Data.Cases.Run_Case Class Reference

Inheritance diagram for SUAVE.Methods.Aerodynamics.AVL.Data.Cases.Run_Case:

Public Member Functions
def	__defaults__ (self)
Public Member Functions inherited from SUAVE.Core.Data.Data
def	__getattribute__ (self, k)
def	__setattr__ (self, k, v)
def	__delattr__ (self, k)
def	__new__ (cls, *args, **kwarg)
def	typestring (self)
def	dataname (self)
def	__str__ (self, indent='')
def	__init__ (self, *args, **kwarg)
def	__iter__ (self)
def	itervalues (self)
def	values (self)
def	update (self, other)
def	append_or_update (self, other)
def	get_bases (self)
def	append (self, value, key=None)
def	deep_set (self, keys, val)
def	deep_get (self, keys)
def	pack_array (self, output='vector')
def	unpack_array (self, M)
def	do_recursive (self, method, other=None, default=None)

Public Attributes
	index
	tag
	mass
	conditions
	stability_and_control
	aero_result_filename_1
	aero_result_filename_2
	aero_result_filename_3
	aero_result_filename_4
	eigen_result_filename_1
	eigen_result_filename_2

Detailed Description

This data class defines the parameters for the analysis cases 
including angle of attack and mach number 

Assumptions:
    None
    
Source:
    None

Inputs:
    None

Outputs:
    None

Properties Used:
    N/A

Member Function Documentation

__defaults__()

def SUAVE.Methods.Aerodynamics.AVL.Data.Cases.Run_Case.__defaults__

(

self

)

Defines the data structure and defaults of aerodynamics coefficients, 
body axis derivatives and stability axis derivatives   

Assumptions:
    None
    
Source:
    None
    
Inputs:
    None
    
Outputs:
    None
    
Properties Used:
    N/A

Reimplemented from SUAVE.Core.Data.Data.

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The documentation for this class was generated from the following file:

• /Users/emiliobotero/Dropbox/SUAVE/SUAVE/trunk/SUAVE/Methods/Aerodynamics/AVL/Data/Cases.py