def ComputeCD0(Aircraft):
#DETERMINE CD0, AND ITERATE FOR THE MTOW ETC.
error = 1
while error > 10e-3:
Sold = Aircraft.ParAnFP.S
AnFP = Aircraft.ParAnFP
AnFP.CD0 = CD0(Aircraft)[0]
Aircraft.ParStruc.MTOW, Aircraft.ParStruc.FW, AnFP.S, AnFP.Thrust,\
AnFP.TtoW,AnFP.WS,AnFP.dfinal,AnFP.tfinal,Conv.ParAnFP.TWactcruise\
= WSandTW(False,Aircraft,ISA_model)
AnFP.Sweep_25, AnFP.Sweep_LE, AnFP.Sweep_50, \
AnFP.b, AnFP.taper, AnFP.c_r, AnFP.c_t,\
AnFP.MAC,AnFP.y_MAC = Wing_Geo(Aircraft)
error = abs((AnFP.S - Sold) / Sold)
CD0_opt = AnFP.CD0
return CD0_opt
def InitSizeSens(Plots, Which_plot, N_cont_lines, N_colours, X_steps, Y_steps):
#INPUTS:
#
#=======================PARAMETERS=============================================
#original parameters
A_org = SensTestAc.ParAnFP.A
e_org = SensTestAc.ParAnFP.e
Range_org = SensTestAc.ParAnFP.s_cruise
hcruise_org = SensTestAc.ParAnFP.h_cruise
payload_org = SensTestAc.ParPayload.m_payload
CD0_org = SensTestAc.ParAnFP.CD0
#wfratioclimb_org = SensTestAc.ParStruc.wfratioclimb
#create lists, these are later used for plotting
A_lst = np.linspace(5, 25, X_steps)
e_lst = np.linspace(0.7, 1., Y_steps)
Range_lst = np.linspace(1500000, 3000000, X_steps)
hcruise_lst = np.linspace(15000, 23000, Y_steps)
payload_lst = np.linspace(5000, 20000, X_steps)
CD0_lst = np.linspace(0.01, 0.05, Y_steps)
wfratioclimb_lst = np.linspace(0.7, 0.99, Y_steps)
oewratio_lst = np.linspace(0.2, 0.7, X_steps)
#==============================================================================
if Plots == True:
# MTOW AND WF PLOTS
#===============================FIRST PLOT=====================================
#for the first plot (MTOW against A and e)
if Which_plot == 1:
#for Fuel Weight & MTOW versus Aspect ratio and Oswald factor
#generate index for first loop
index_y = -1
#initialise 2d arrays for plotting values
MTOW_lst = np.zeros((X_steps, Y_steps))
wf_ratio_lst = np.zeros((X_steps, Y_steps))
for i in A_lst:
print(i)
#generate index for second loop
index_x = -1
index_y = index_y + 1
A = i
for j in e_lst:
index_x = index_x + 1
e = j
#adjust A and e
SensTestAc.ParAnFP.A = A
SensTestAc.ParAnFP.e = e
#determine MTOW and wf for this aspect ratio
MTOW = WSandTW(False, SensTestAc, ISA_model)[0]
#MTOW = WSandTW(aero, struct)
wf_ratio = WSandTW(False, SensTestAc, ISA_model)[1]
#append values to the appropriate lists
MTOW_lst[index_y, index_x] = MTOW
wf_ratio_lst[index_y, index_x] = wf_ratio
#reset to original values:
SensTestAc.ParAnFP.A = A_org
SensTestAc.ParAnFP.e = e_org
#plotting
Z = np.array(MTOW_lst)
W = np.array(wf_ratio_lst)
X, Y = np.meshgrid(e_lst, A_lst)
fig, ax = plt.subplots()
CS = ax.contour(X,Y,Z,N_cont_lines,colors =['#FFFFFF', '#FFFFFF',\
'#FFFFFF', '#FFFFFF','#000000','#000000','#000000','#000000'])
firstplot = ax.contourf(X, Y, W, N_colours, cmap='gray')
#labels and axes and stuff
cbar = fig.colorbar(firstplot, orientation="vertical", pad=0.2)
cbar.ax.invert_yaxis()
ax.set_xlabel('Oswald factor [-]')
ax.set_ylabel('Aspect ratio [-]')
labels = ['MTOW [kg]']
CS.collections[0].set_label(labels[0])
CS.collections[4].set_label(labels[0])
#for final version, set manual = True
ax.clabel(CS, fontsize=9, inline=1, manual=False)
cbar.set_label('Fuel Weight[kg]', labelpad=-40, y=1.05, rotation=0)
plt.legend(loc='upper left')
plt.show()
#==============================================================================
#===============================SECOND PLOT====================================
#for the second plot (MTOW against Range and altitude)
if Which_plot == 2:
#generate index for first loop
index_y = -1
#initialise 2d arrays for plotting values
MTOW_lst = np.zeros((X_steps, Y_steps))
wf_ratio_lst = np.zeros((X_steps, Y_steps))
for i in Range_lst:
print(i)
#generate index for second loop
index_x = -1
index_y = index_y + 1
Range = i
for j in hcruise_lst:
index_x = index_x + 1
hcruise = j
#adjust A and e
SensTestAc.ParAnFP.h_cruise = hcruise
SensTestAc.ParAnFP.s_cruise = Range
#determine MTOW and wf for this aspect ratio
MTOW = WSandTW(False, SensTestAc, ISA_model)[0]
#MTOW = WSandTW(aero, struct)
wf_ratio = WSandTW(False, SensTestAc, ISA_model)[1]
#append values to the appropriate lists
MTOW_lst[index_y, index_x] = MTOW
wf_ratio_lst[index_y, index_x] = wf_ratio
#reset to original values:
SensTestAc.ParAnFP.h_cruise = hcruise_org
SensTestAc.ParAnFP.s_cruise = Range_org
#plotting
Z = np.array(MTOW_lst)
W = np.array(wf_ratio_lst)
X, Y = np.meshgrid(hcruise_lst, Range_lst)
fig, ax = plt.subplots()
CS = ax.contour(X,Y,Z,N_cont_lines,colors =['#FFFFFF', '#FFFFFF',\
'#FFFFFF', '#FFFFFF','#000000','#000000','#000000','#000000'])
firstplot = ax.contourf(X, Y, W, N_colours, cmap='gray')
#labels and axes and stuff
cbar = fig.colorbar(firstplot, orientation="vertical", pad=0.2)
cbar.ax.invert_yaxis()
ax.set_xlabel('altitude [m]')
ax.set_ylabel('range [m]')
labels = ['MTOW [kg]']
CS.collections[0].set_label(labels[0])
CS.collections[4].set_label(labels[0])
#for final version, set manual = True
ax.clabel(CS, fontsize=9, inline=1, manual=False)
cbar.set_label('Fuel Weight [kg]',
labelpad=-40,
y=1.05,
rotation=0)
plt.legend(loc='upper left')
plt.show()
#==============================================================================
#===============================THIRD PLOT====================================
if Which_plot == 3:
#generate index for first loop
index_y = -1
#initialise 2d arrays for plotting values
MTOW_lst = np.zeros((X_steps, Y_steps))
wf_ratio_lst = np.zeros((X_steps, Y_steps))
for i in payload_lst:
#generate index for second loop
index_x = -1
index_y = index_y + 1
payload = i
for j in CD0_lst:
index_x = index_x + 1
CD0 = j
#adjust A and e
SensTestAc.ParAnFP.CD0 = CD0
SensTestAc.ParPayload.m_payload = payload
#determine MTOW and wf for this aspect ratio
MTOW = WSandTW(False, SensTestAc, ISA_model)[0]
#MTOW = WSandTW(aero, struct)
wf_ratio = WSandTW(False, SensTestAc, ISA_model)[1]
#append values to the appropriate lists
MTOW_lst[index_y, index_x] = MTOW
wf_ratio_lst[index_y, index_x] = wf_ratio
#reset to original values
SensTestAc.ParAnFP.CD0 = CD0_org
SensTestAc.ParPayload.m_payload = payload_org
#plotting
Z = np.array(MTOW_lst)
W = np.array(wf_ratio_lst)
X, Y = np.meshgrid(CD0_lst, payload_lst)
fig, ax = plt.subplots()
CS = ax.contour(X,Y,Z,N_cont_lines,colors =['#FFFFFF', '#FFFFFF',\
'#FFFFFF', '#FFFFFF','#000000','#000000','#000000','#000000'])
firstplot = ax.contourf(X, Y, W, N_colours, cmap='gray')
#labels and axes and stuff
cbar = fig.colorbar(firstplot, orientation="vertical", pad=0.2)
cbar.ax.invert_yaxis()
ax.set_xlabel('CD0 [-]')
ax.set_ylabel('payload mass [kg]')
labels = ['MTOW [kg]']
CS.collections[0].set_label(labels[0])
CS.collections[4].set_label(labels[0])
#for final version, set manual = True
ax.clabel(CS, fontsize=9, inline=1, manual=False)
cbar.set_label('Fuel Weight[kg]', labelpad=-40, y=1.05, rotation=0)
plt.legend(loc='upper left')
plt.show()
#==============================================================================
# S AND TW PLOTS
#===============================FOURTH PLOT====================================
if Which_plot == 4:
#for Fuel Weight & MTOW versus Aspect ratio and Oswald factor
#generate index for first loop
index_y = -1
#initialise 2d arrays for plotting values
S_lst = np.zeros((X_steps, Y_steps))
TW_lst = np.zeros((X_steps, Y_steps))
for i in A_lst:
#generate index for second loop
index_x = -1
index_y = index_y + 1
A = i
for j in e_lst:
index_x = index_x + 1
e = j
#adjust A and e
SensTestAc.ParAnFP.A = A
SensTestAc.ParAnFP.e = e
#determine MTOW and wf for this aspect ratio
S = WSandTW(False, SensTestAc, ISA_model)[2]
#MTOW = WSandTW(aero, struct)
TW = WSandTW(False, SensTestAc, ISA_model)[3]
#append values to the appropriate lists
S_lst[index_y, index_x] = S
TW_lst[index_y, index_x] = TW
#reset to original values:
SensTestAc.ParAnFP.A = A_org
SensTestAc.ParAnFP.e = e_org
#plotting
Z = np.array(S_lst)
W = np.array(TW_lst)
X, Y = np.meshgrid(e_lst, A_lst)
fig, ax = plt.subplots()
CS = ax.contour(X,Y,Z,N_cont_lines,colors =['#FFFFFF', '#FFFFFF',\
'#FFFFFF', '#FFFFFF','#000000','#000000','#000000','#000000'])
firstplot = ax.contourf(X, Y, W, N_colours, cmap='gray')
#labels and axes and stuff
cbar = fig.colorbar(firstplot, orientation="vertical", pad=0.2)
cbar.ax.invert_yaxis()
ax.set_xlabel('Oswald factor [-]')
ax.set_ylabel('Aspect ratio [-]')
labels = ['Wing surface [m2]']
CS.collections[0].set_label(labels[0])
CS.collections[4].set_label(labels[0])
#for final version, set manual = True
ax.clabel(CS, fontsize=9, inline=1, manual=False)
cbar.set_label('Thrust [N]', labelpad=-40, y=1.05, rotation=0)
plt.legend(loc='upper left')
plt.show()
if Which_plot == 5:
#generate index for first loop
index_y = -1
#initialise 2d arrays for plotting values
S_lst = np.zeros((X_steps, Y_steps))
TW_lst = np.zeros((X_steps, Y_steps))
for i in Range_lst:
#generate index for second loop
index_x = -1
index_y = index_y + 1
Range = i
for j in hcruise_lst:
index_x = index_x + 1
hcruise = j
#adjust A and e
SensTestAc.ParAnFP.h_cruise = hcruise
SensTestAc.ParAnFP.s_cruise = Range
#determine MTOW and wf for this aspect ratio
S = WSandTW(False, SensTestAc, ISA_model)[2]
#MTOW = WSandTW(aero, struct)
TW = WSandTW(False, SensTestAc, ISA_model)[3]
#append values to the appropriate lists
S_lst[index_y, index_x] = S
TW_lst[index_y, index_x] = TW
#reset to org values
SensTestAc.ParAnFP.h_cruise = hcruise_org
SensTestAc.ParAnFP.s_cruise = Range_org
#plotting
Z = np.array(S_lst)
W = np.array(TW_lst)
X, Y = np.meshgrid(hcruise_lst, Range_lst)
fig, ax = plt.subplots()
CS = ax.contour(X,Y,Z,N_cont_lines,colors =['#FFFFFF', '#FFFFFF',\
'#FFFFFF', '#FFFFFF','#000000','#000000','#000000','#000000'])
firstplot = ax.contourf(X, Y, W, N_colours, cmap='gray')
#labels and axes and stuff
cbar = fig.colorbar(firstplot, orientation="vertical", pad=0.2)
cbar.ax.invert_yaxis()
ax.set_xlabel('altitude [m]')
ax.set_ylabel('range [m]')
labels = ['Wing surface [m2]']
CS.collections[0].set_label(labels[0])
CS.collections[4].set_label(labels[0])
#for final version, set manual = True
ax.clabel(CS, fontsize=9, inline=1, manual=False)
cbar.set_label('Thrust [N]', labelpad=-40, y=1.05, rotation=0)
plt.legend(loc='upper left')
plt.show()
if Which_plot == 6:
#generate index for first loop
index_y = -1
#initialise 2d arrays for plotting values
S_lst = np.zeros((X_steps, Y_steps))
TW_lst = np.zeros((X_steps, Y_steps))
for i in payload_lst:
#generate index for second loop
index_x = -1
index_y = index_y + 1
payload = i
for j in CD0_lst:
index_x = index_x + 1
CD0 = j
SensTestAc.ParAnFP.CD0 = CD0
SensTestAc.ParPayload.m_payload = payload
#determine MTOW and wf for this aspect ratio
S = WSandTW(False, SensTestAc, ISA_model)[2]
#MTOW = WSandTW(aero, struct)
TW = WSandTW(
False, SensTestAc,
ISA_model)[3] #append values to the appropriate lists
S_lst[index_y, index_x] = S
TW_lst[index_y, index_x] = TW
#reset to org values
SensTestAc.ParAnFP.CD0 = CD0_org
SensTestAc.ParPayload.m_payload = payload_org
#plotting
Z = np.array(S_lst)
W = np.array(TW_lst)
X, Y = np.meshgrid(CD0_lst, payload_lst)
fig, ax = plt.subplots()
CS = ax.contour(X,Y,Z,N_cont_lines,colors =['#FFFFFF', '#FFFFFF',\
'#FFFFFF', '#FFFFFF','#000000','#000000','#000000','#000000'])
firstplot = ax.contourf(X, Y, W, N_colours, cmap='gray')
#labels and axes and stuff
cbar = fig.colorbar(firstplot, orientation="vertical", pad=0.2)
cbar.ax.invert_yaxis()
ax.set_xlabel('CD0 [-]')
ax.set_ylabel('payload mass [kg]')
labels = ['Wing surface [m2]']
CS.collections[0].set_label(labels[0])
CS.collections[4].set_label(labels[0])
#for final version, set manual = True
ax.clabel(CS, fontsize=9, inline=1, manual=False)
cbar.set_label('Thrust [N]', labelpad=-40, y=1.05, rotation=0)
plt.legend(loc='upper left')
plt.show()
# =============================================================================
# RESERVE CONFIGURATION
if Which_plot == 7:
#generate index for first loop
index_y = -1
#initialise 2d arrays for plotting values
MTOW_lst = np.zeros((X_steps, Y_steps))
wf_ratio_lst = np.zeros((X_steps, Y_steps))
for i in payload_lst:
#generate index for second loop
index_x = -1
index_y = index_y + 1
payload = i
for j in oewratio_lst:
index_x = index_x + 1
OEWratio = j
#adjust A and e
SensTestAc.ParStruc.OEWratio = OEWratio
SensTestAc.ParPayload.m_payload = payload
#determine MTOW and wf for this aspect ratio
MTOW = WSandTW(False, SensTestAc, ISA_model)[2]
#MTOW = WSandTW(aero, struct)
wf_ratio = WSandTW(False, SensTestAc, ISA_model)[3]
#append values to the appropriate lists
MTOW_lst[index_y, index_x] = MTOW
wf_ratio_lst[index_y, index_x] = wf_ratio
#reset to original values:
#SensTestAc.ParStruc = wfratioclimb_org
SensTestAc.ParAnFP.s_cruise = Range_org
#plotting
Z = np.array(MTOW_lst)
W = np.array(wf_ratio_lst)
X, Y = np.meshgrid(oewratio_lst, payload_lst)
fig, ax = plt.subplots()
CS = ax.contour(X,Y,Z,N_cont_lines,colors =['#FFFFFF', '#FFFFFF',\
'#FFFFFF', '#FFFFFF','#000000','#000000','#000000','#000000'])
firstplot = ax.contourf(X, Y, W, N_colours, cmap='gray')
#labels and axes and stuff
cbar = fig.colorbar(firstplot, orientation="vertical", pad=0.2)
cbar.ax.invert_yaxis()
ax.set_xlabel('OEW/MTOW [-]')
ax.set_ylabel('payload mass [kg]')
labels = ['Wing surface [m^2]']
CS.collections[0].set_label(labels[0])
CS.collections[4].set_label(labels[0])
#for final version, set manual = True
ax.clabel(CS, fontsize=9, inline=1, manual=False)
cbar.set_label('Thrust [N]', labelpad=-40, y=1.05, rotation=0)
plt.legend(loc='upper left')
plt.show()
return (0)
def test_WSandTW():
out = WSandTW(False, Conv,ISA_model)
assert (np.isclose(out[0],Conv.ParStruc.MTOW))
def InitSizeSens(Plots, Which_plot, N_cont_lines, N_colours, X_steps, Y_steps):
#INPUTS:
#
#=======================PARAMETERS=============================================
#create lists, these are later used for plotting
A_lst = np.linspace(5, 25, X_steps)
e_lst = np.linspace(0.5, 1., Y_steps)
Range_lst = np.linspace(1000000, 4000000, X_steps)
hcruise_lst = np.linspace(10000, 23000, Y_steps)
payload_lst = np.linspace(5000, 20000, X_steps)
CD0_lst = np.linspace(0.01, 0.05, Y_steps)
#==============================================================================
if Plots == True:
# MTOW AND WF PLOTS
#===============================FIRST PLOT=====================================
#for the first plot (MTOW against A and e)
if Which_plot == 1:
#for Fuel Weight & MTOW versus Aspect ratio and Oswald factor
# =============================================================================
# Range = par.get('s_cruise')
# hcruise = par.get('h_cruise')
# CD0 = par.get('C_D_0_conv')
# payload = par.get('m_payload')
# =============================================================================
#generate index for first loop
index_y = -1
#initialise 2d arrays for plotting values
MTOW_lst = np.zeros((X_steps, Y_steps))
wf_ratio_lst = np.zeros((X_steps, Y_steps))
for i in A_lst:
#generate index for second loop
index_x = -1
index_y = index_y + 1
A = i
for j in e_lst:
index_x = index_x + 1
e = j
#adjust A and e
SensTestAc.ParAnFP.A = A
SensTestAc.ParAnFP.e = e
#determine MTOW and wf for this aspect ratio
MTOW = WSandTW(False, SensTestAc, ISA_model)[0]
#MTOW = WSandTW(aero, struct)
wf_ratio = WSandTW(False, SensTestAc, ISA_model)[1]
#append values to the appropriate lists
MTOW_lst[index_y, index_x] = MTOW
wf_ratio_lst[index_y, index_x] = wf_ratio
#plotting
Z = np.array(MTOW_lst)
W = np.array(wf_ratio_lst)
X, Y = np.meshgrid(e_lst, A_lst)
fig, ax = plt.subplots()
CS = ax.contour(X, Y, Z, N_cont_lines, colors='k')
firstplot = ax.contourf(X, Y, W, N_colours, cmap='jet')
#labels and axes and stuff
cbar = fig.colorbar(firstplot, orientation="vertical", pad=0.2)
cbar.ax.invert_yaxis()
ax.set_xlabel('Oswald factor [-]')
ax.set_ylabel('Aspect ratio [-]')
labels = ['MTOW [kg]']
CS.collections[0].set_label(labels[0])
#for final version, set manual = True
ax.clabel(CS, fontsize=9, inline=1, manual=False)
cbar.set_label('Fuel Weight/MTOW',
labelpad=-40,
y=1.05,
rotation=0)
plt.legend(loc='upper left')
plt.show()
Conv.ParAnFP.e = 0.85
Conv.ParAnFP.CD0 = 0.02
Conv.ParAnFP.M_cruise = 0.7
Conv.ParAnFP.Mdd = 0.7
#parameters from functions
#ANFP parameters
Conv.ParAnFP.s_cruise = CruiseRange(Conv)
Conv.ParAnFP.t_cruise = CruiseTime(Conv, ISA_model)
Conv.ParAnFP.V_cruise = Conv.ParAnFP.Get_V_cruise()
Conv.ParPayload.disperRatePerTime = (Conv.ParPayload.m_sulphur
/Conv.ParAnFP.t_cruise)
Conv.ParAnFP.S = WSandTW(False,Conv,ISA_model)[2]
Conv.ParAnFP.TtoW = WSandTW(False,Conv,ISA_model)[3]
#structures parameters
Conv.ParStruc.MTOW = WSandTW(False,Conv,ISA_model)[0]
Conv.ParStruc.FW = WSandTW(False,Conv,ISA_model)[1]
Conv.Par
# ===============================CONFIGURATION 2===============================
#Other configuration example:
BWB = Aircraft()
def ClassIAircraft():
#Parameters not determined from functionss
Conv.ParAnFP.A = 14.38
Conv.ParAnFP.CD0 = 0.015
Conv.ParAnFP.e = 0.85
Conv.ParAnFP.M_cruise = 0.7
Conv.ParAnFP.Mdd = 0.7
Conv.ParAnFP.T_to = 200000
#Parameters useful to class II estimation
Conv.ParAnFP.n_engines = 2 #Number of wing mounted engines
Conv.ParAnFP.wm_un = 0 #Undercarriage in the wing on (1) or off (0)
#Conv.ParAnFP.CD0 = 0.008
Conv.ParAnFP.We = 2484 #[kg] weight per engine
#parameters from functions
##ANFP parameters
Conv.ParAnFP.s_cruise = CruiseRange(Conv)
Conv.ParAnFP.t_cruise = CruiseTime(Conv, ISA_model)
Conv.ParAnFP.V_cruise = Conv.ParAnFP.Get_V_cruise()
Conv.ParPayload.disperRatePerTime = (Conv.ParPayload.m_payload /
Conv.ParAnFP.t_cruise)
Conv.ParAnFP.Extrarange = 500 * 10**3 #[m]
Conv.ParStruc.MTOW, Conv.ParStruc.FW, Conv.ParAnFP.S, Conv.ParAnFP.Thrust, Conv.ParAnFP.TtoW, Conv.ParAnFP.WS, \
Conv.ParAnFP.dclimbcruise, Conv.ParAnFP.tclimbcruise, Conv.ParAnFP.TWactcruise = WSandTW(False,Conv,ISA_model)
Conv.ParStruc.wfratio = Conv.ParStruc.FW / Conv.ParStruc.MTOW
#Conv.ParAnFP.CD0 = 0.008
Conv.ParAnFP.We = 2484 #[kg] weight per engine
#parameters from functions
##ANFP parameters
Conv.ParAnFP.s_cruise = CruiseRange(Conv)
Conv.ParAnFP.t_cruise = CruiseTime(Conv, ISA_model)
Conv.ParAnFP.V_cruise = Conv.ParAnFP.Get_V_cruise()
Conv.ParPayload.disperRatePerTime = (Conv.ParPayload.m_payload /
Conv.ParAnFP.t_cruise)
Conv.ParAnFP.Extrarange = 500 * 10**3 #[m]
Conv.ParStruc.MTOW, Conv.ParStruc.FW, Conv.ParAnFP.S, Conv.ParAnFP.Thrust, Conv.ParAnFP.TtoW, Conv.ParAnFP.WS, \
Conv.ParAnFP.dclimbcruise, Conv.ParAnFP.tclimbcruise = WSandTW(False,Conv,ISA_model)[:-1]
#Geometry: Sweep 0.25, le, 0.50 in radians, Span in meters, taper ratio, root, tip , MAC in meters
Conv.ParAnFP.Sweep_25, Conv.ParAnFP.Sweep_LE, Conv.ParAnFP.Sweep_50, Conv.ParAnFP.b,Conv.ParAnFP.taper,\
Conv.ParAnFP.c_r, Conv.ParAnFP.c_t, Conv.ParAnFP.MAC, Conv.ParAnFP.y_MAC = Wing_Geo(Conv)
#Airfoil parameters
# =============================================================================
# Conv.ParAnFP.cl_alpha = Airfoil(Conv)[0] #clalpha [/deg]
# Conv.ParAnFP.cl_max = Airfoil(Conv)[1] #maximum lift coefficient of airfoil [-]
# Conv.ParAnFP.tc = Airfoil(Conv)[2] #thickness to chord ratio [-]
# Conv.ParAnFP.CD0_airfoil = Airfoil(Conv)[3] #zero-lift drag [-]
# =============================================================================
Conv.ParAnFP.cl_alpha, Conv.ParAnFP.cl_max, Conv.ParAnFP.tc, Conv.ParAnFP.Cd0, Conv.ParAnFP.cm_0 = Airfoil(
Conv)