def plot_results():
ac = DesignFormulation()
ac.load_xls('Baseline1')
# baseline
ac.setup()
ac.gvfmAero = True
x0 = ac.wing.x2d
y0 = ac.wing.y2d
cg0 = ac.get_cg()
xbase = ac.x0norm
ac.set_x(xbase)
ac.show_results()
print ac.get_drag()
# low fidelity optimum
xopt1 = np.array([ 0.20520747,-0.39226611,-0.47326701,-1.,0.14291925,0.98650447,
0.37346922, 0.37756372, 0.65654722])
print 'Low fidelity optimum\n==========='
ac.set_x(xopt1)
ac.show_results()
print ac.get_drag()
x1 = ac.wing.x2d
y1 = ac.wing.y2d
cg1 = ac.get_cg()
xgvfm1 = np.array([-0.10127195,-0.10127187,-0.60597138,-0.99999966,-0.71421434,0.97300896, 1.00000803, 0.57455958,0.3130853])
xgvfm2 = np.array([-0.04819471,-0.04819471,-0.59713618,-0.99999966,-1.,0.94601792,1.00000803,0.81889676,-0.3738294])
xgvfm4 = np.array([-0.10676065, -0.10676065, -0.61007048, -1.00003353, -0.57133293, 0.9857291, 1.00000803, 0.56576939, 0.08997523])
print np.linalg.norm(xgvfm1-xgvfm2)
ac.set_x(xgvfm4)
print ac.get_cg()
print ac.wing.area
print ac.wing.MAC
print ac.wing.span
ac.show_results()
print ac.get_drag()
x3 = ac.wing.x2d
y3 = ac.wing.y2d
cg3 = ac.get_cg()
fig = plt.figure(1)
ax1 = fig.add_subplot(111)
ax1.hold(True)
ax1.axis('equal')
ax1.plot(x0,y0,'ko-',linewidth=2)
ax1.plot(x1,y1,'b^:',linewidth=2)
ax1.plot(x3,y3,'rs--',linewidth=2)
#plt.plot(x2,y2,'k-')
ax1.plot(0,-cg0[0],'ko')
ax1.plot(0,-cg1[0],'b^')
ax1.plot(0,-cg3[0],'rs')
ax1.legend(['Baseline','Low-fi optimum','GVFM optimum'])
#plt.plot(0,-cg2[0],'ko')
plt.show()
def create_input_files():
from ucav_design_1 import DesignFormulation
# Longitudinal (half wing)
doePath = r'D:\1. Current work\2014 - UAV performance code\Results\norm_results.txt'
#DOE = read_tabulated_data_without_header('LHS_dvar9_sample30.txt')
DOE = read_tabulated_data_without_header(doePath)
ac = DesignFormulation()
ac.load_xls('Baseline1')
ac.setup()
startCase = 30
# Mach = ac.designGoals.cruiseMach
# altitude = ac.designGoals.cruiseAltitude
yplus = .5
wdir = 'D:\CFD'
alpha = [-2,0,2]
# beta = 2.0
niter = 5000
batFileLongitudinal = '%s\\batchCFD.bat'%wdir
fid = open(batFileLongitudinal,'at')
pathFluent = r'C:\Program Files\Ansys Inc\v130\fluent\ntbin\win64\fluent.exe'
for i,xnorm in enumerate(DOE):
if i>0:
name = '%s\\case%d'%(wdir,i+startCase)
caseName = 'case%d'%(i+startCase)
print name
ac.set_x(xnorm,False)
print ac.xCurrent
raw_input()
#FIXME: this part adds section for payload on top
#ac._adjust_root_airfoil()
ac.save_2d_figure('%s.png'%name)
igsPath = '%s.igs'%name
symCasPath = '%s_sym.cas'%name
nonsymCasPath = '%s_half.cas'%name
glfPath = '%s.glf'%name
#create_catia_wing(ac,igsPath)
create_fw_cmesh(ac,igsPath,symCasPath,nonsymCasPath,yplus,glfPath)
Sref = ac.wing.area/2.0
Cref = ac.wing.MAC
#Lref = ac.wing.span
ac._restore_root_airfoil()
CG = ac.get_cg()
#a = 2.0
# outPrefix = '%s\\results\\case%d_sym_a%d_b%d'%(wdir,i+1,a*100,beta*100)
# journalFileRel = 'case%d_sym_a%d_b%d.jou'%(i+1, a*100,beta*100)
# journalFile = '%s_sym_a%d_b%d.jou'%(name, a*100, beta*100)
#run_wing_half(symCasPath, outPrefix, ac.designGoals.fc, a, beta, Sref, Lref, CG, journalFile, niter)
for a in alpha:
outPrefix = '%s\\results\\%s_half_a%d'%(wdir,caseName,a*100)
journalFileRel = '%s_half_a%d.jou'%(name, a*100)
journalFile = '%s_half_a%d.jou'%(name, a*100)
run_wing_half(nonsymCasPath, outPrefix, ac.designGoals.fc, a, 0,
Sref, Cref, CG,journalFile,niter)
fid.write('\"%s\" 3ddp -t8 -i %s -wait\n'%(pathFluent, journalFileRel))
fid.close()
