Python Wing_param.get_AR Examples

Example #1

File: Induced_drag_theoretical.py Project: regislebrun/DLLM

wing_param.set_value('root_chord',4.)
wing_param.set_value('root_height',0.0)
wing_param.set_value('tip_height',0.0)
wing_param.build_linear_airfoil(OC, AoA0=0., Cm0=-0.1, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()

airfoils=wing_param.get_linked_airfoils()
Cla=airfoils[24].ClAlpha(0.0,0.3)

print "Cla=",Cla

#list_file = ['SimpleRect_3.00E-01.dat','SimpleRect_6.00E-01.dat','SimpleRect_8.00E-01.dat']
list_file = ['Elliptic_2.00E-01.dat']
e=0.70
AR = wing_param.get_AR()
print 'AR=',AR

for i,file_name in enumerate(list_file):
    fid=open(file_name,'r')
    lines=fid.readlines()
    fid.close()
    
    fid=open('Cdp_'+file_name,'w')
    for j,line in enumerate(lines):
        words=string.split(line)
        new_words=words
        if j == 1:
            new_words = ['#','AoA','Cl','Cdp','Cl_theory','Cdp_theory','Cdp_elliptic']
        if len(words)> 0:
            if words[0] != '#':

Example #2

File: Rect_sweep0.py Project: FrancoisGallard/DLLM

OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()

wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',40.)
wing_param.set_value('sweep',0.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',1.0)
wing_param.set_value('break_chord',1.0)
wing_param.set_value('tip_chord',1.0)
wing_param.set_value('root_height',0.15)
wing_param.set_value('break_height',0.15)
wing_param.set_value('tip_height',0.15)
wing_param.build_linear_airfoil(OC, AoA0=0., Cm0=0.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()

print wing_param

print 'AR=',wing_param.get_AR()

DLLM = DLLMTargetCl('Rectsweep0',wing_param,OC)
DLLM.set_target_Cl(0.5)
DLLM.run_direct()
DLLM.run_post()

Example #3

OC.set_P0(101325.)
OC.set_humidity(0.)
OC.compute_atmosphere()

wing_param=Wing_param('test_param',geom_type='Broken',n_sect=20)
wing_param.build_wing()
wing_param.set_value('span',3.)
wing_param.set_value('sweep',30.)
wing_param.set_value('break_percent',33.)
wing_param.set_value('root_chord',1.0)
wing_param.set_value('break_chord',1.0)
wing_param.set_value('tip_chord',1.0)
wing_param.set_value('root_height',0.15)
wing_param.set_value('break_height',0.15)
wing_param.set_value('tip_height',0.15)
wing_param.build_linear_airfoil(OC, AoA0=0., Cm0=0.0, set_as_ref=True)
wing_param.build_airfoils_from_ref()
wing_param.update()

print wing_param

print 'AR=',wing_param.get_AR()

DLLM = DLLMTargetCl('RectLowARsweep30',wing_param,OC)
DLLM.set_target_Cl(0.5)
DLLM.run_direct()
DLLM.run_post()