def __init__(self, database=None, relative_thickness=0.15, interpolator='2DSpline',Sref=1., Lref=1.):
'''
Constructor for a polar of a simple airfoil.
@param Sref : reference surface
@param Lref : reference length
@param database : the dataBase in which the discrete values are stored, or None
'''
Airfoil.__init__(self,Sref,Lref,relative_thickness)
# self.__database=database
# self.__fd_database=Database()
if interpolator == '2DSpline':
print "building new spline 2D Interpolator"
x,y=self.__database.get_all_in_outs(self.DATABASE_ABSCISSA_TAG,self.DATABASE_AERO_COEFS_TAG)
y=array(y).T
x=array(x)
scale=array([1.,1.])
self.__cl_interpolator=Spline2D_interpolator(array(x),array(y[0,:]),scale)
self.__cd_interpolator=Spline2D_interpolator(array(x),array(y[1,:]),scale)
self.__cm_interpolator=Spline2D_interpolator(array(x),array(y[2,:]),scale)
print "Done."
else:
self.__cl_interpolator=aero_coefs_interpolator[0]
self.__cd_interpolator=aero_coefs_interpolator[1]
self.__cm_interpolator=aero_coefs_interpolator[2]
def __init__(self, OC, AoA0=0., Sref=1., Lref=1., rel_thick=0.0, sweep=0.0, pcop=0.25, Ka=0.95, grad_active=True):
'''
Constructor for airfoils
@param AoA0:angle of attack of null lift
@param Cd0 : drag
@param Cm0 : pitch moment
@param relative_thickness : relative thickness for addition of a correction of ClAlpha
@param Sref : reference surface
@param Lref : reference length
'''
if rel_thick<0. or rel_thick>0.30:
raise Exception, "Relative thickness must be >0. and <0.30"
Airfoil.__init__(self, OC, Lref=Lref, Sref=Sref, grad_active=grad_active)
self.__AoA0_deg = None
self.__AoA0 = None
self.set_AoA0(AoA0)
self.__Ka = None
self.set_Ka(Ka)
self.__rel_thick = None
self.__rel_thick_grad = None
self.set_rel_thick(rel_thick)
self.__sweep = None
self.__sweep_grad = None
self.set_sweep(sweep)
self.pcop = pcop
def __init__(self, OC, surrogate_model, relative_thickness=.12, camber=0., Sref=1., Lref=1., sweep=0., surrogate_fcs=None):
Airfoil.__init__(self, OC, Sref, Lref, relative_thickness, sweep, camber)
if not surrogate_fcs:
self.__coefs = SurrogateCoefs(surrogate_model)
else:
self.__coefs = surrogate_fcs
self.__surrogate_model = surrogate_model
def __init__(self, controls=None, proxy=None,
pos = Vector3(0,0,0),
attitude = Quaternion(0.5, -0.5, 0.5, 0.5),
velocity = Vector3(0,0,0),
thrust = 0, ident=None):
global cterrain
Airfoil.__init__(self, pos, attitude, velocity, thrust, cterrain)
ControlledSer.__init__(self, MyAirfoil.TYP, ident, proxy)
self.setControls(controls)
def __init__(self,
controls=None,
proxy=None,
pos=Vector3(0, 0, 0),
attitude=Quaternion(0.5, -0.5, 0.5, 0.5),
velocity=Vector3(0, 0, 0),
thrust=0,
ident=None):
global cterrain
Airfoil.__init__(self, pos, attitude, velocity, thrust, cterrain)
ControlledSer.__init__(self, MyAirfoil.TYP, ident, proxy)
self.setControls(controls)
def __init__(self, OC, AoA0=0., Cm0=0.0, Sref=1., Lref=1., rel_thick=0.0, sweep=0.0, Ka=0.95):
'''
Constructor for airfoils
@param AoA0:angle of attack of null lift
@param Cd0 : drag
@param Cm0 : pitch moment
@param relative_thickness : relative thickness for addition of a correction of ClAlpha
@param Sref : reference surface
@param Lref : reference length
'''
if rel_thick<0. or rel_thick>0.25:
raise Exception, "Relative thickness must be >0. and <0.25"
Airfoil.__init__(self,OC, Sref,Lref,rel_thick,sweep)
self.__AoA0 = AoA0*np.pi/180.
self.__Cm0 = Cm0
self.__Ka = Ka
def __init__(self,
OC,
surrogate_model,
relative_thickness=.12,
camber=0.,
Sref=1.,
Lref=1.,
sweep=0.,
surrogate_fcs=None):
Airfoil.__init__(self, OC, Sref, Lref, relative_thickness, sweep,
camber)
if not surrogate_fcs:
self.__coefs = SurrogateCoefs(surrogate_model)
else:
self.__coefs = surrogate_fcs
self.__surrogate_model = surrogate_model
def __init__(self, OC, Sref=1., Lref=1., y_pos=None, grad_active=False):
'''
Constructor for airfoils
@param y_pos : span-wise position for interpolation
@param Sref : reference surface
@param Lref : reference length
'''
Airfoil.__init__(self, OC, Lref=Lref, Sref=Sref, grad_active=grad_active)
self.y_pos = y_pos
self.__y_def_list = None
self.__file_def_list = None
self.__interp_list = None
self.__index_p = None
self.__index_m = None
self.__fact_p = None
self.__fact_m = None
