def optWellPressures(self, WHP=1, phaseCheck=False):
"""
:param WHP : trazeni tlak na uscu
:return: tlak fluida na uscu (bar) i snaga pumpe potrebna za podizanje tlaka na tu razinu (W)
"""
if WHP < 1:
WHP = 1e5
else:
WHP = WHP * 1e5
g = 9.8066 # akceleracija zbog gravitacije m2/s
p = self.p_i * 1e5 # pocetni tlak (dno busotine, Pa)
if not self.proizvodna:
p = p - WHP # oduzeti tlak na wellheadu ukoliko postoji
e, eD = self.e, self.eD
pg, Reg, flow_type, dens, mu, dpf, ro = [], [], [], [], [], 0, 0
pump = 0
for zi in self.z:
self.p.append(p)
ro = CP.PropsSI('D', 'T', (273.15 + self.T), 'P', p,
self.fluid) # gustoca pri trenutnom tlaku
mi = CP.PropsSI('V', 'T', (273.15 + self.T), 'P', p,
self.fluid) # viskoznost pri trenutnom tlaku
self.ro.append(ro)
self.mi.append(mi)
q_rc = self.q * self.ro_sc / ro # volumni protok u busotini pri zadanoj gustoci i protoku na povrsini
v = q_rc / (np.pi * 0.25 * self.d**2) # brzina protjecanja m/s
Re = self.funcRe(ro, v, self.d, mi) # Reynoldsov broj
self.Re_i.append(Re)
self.flowType.append(self.funcReg(Re, e))
f = fluids.friction_factor(
Re=Re, eD=eD) # Clamondova jednadzba - bolja od Haalandove
# Clamond, Didier, 2009. “Efficient Resolution of the Colebrook Equation.”
self.fr.append(f)
dpf = self.funcdpf(f, self.dz, self.d, ro, v)
if self.proizvodna:
dp = ro * g * self.dz - ro * v * self.dz + dpf
else:
dp = ro * g * self.dz + ro * v * self.dz - dpf
p = p - dp
if (p < 101325 and self.proizvodna):
self.info = 'izlaz na:' + str(zi) + ' m \n'
ro_avg = (ro + CP.PropsSI('D', 'T', (273.15 + self.T), 'P',
WHP, self.fluid)) * 0.5
pump = zi * ro_avg * g + WHP
break
if (self.proizvodna == False):
self.info = ''
ro_avg = (
ro + CP.PropsSI('D', 'T',
(273.15 + self.T), 'P', WHP, self.fluid)) * 0.5
pump = p - WHP
self.info += 'potrebno pumpati: ' + str(pump) + ' Pa \n'
self.info += 'ro_avg = ' + str(ro_avg) + ' kg/m3 \n'
self.Ppump = self.q * pump * 0.001 # snaga pumpe, kW
self.info += 'Potrebna snaga pumpe = ' + str(self.Ppump) + ' kW \n'
def time_friction_factor_S2(self):
friction_factor(Re=2.9E5, eD=1E-5, Method='Serghides_2')
def time_friction_factor(self):
friction_factor(Re=1E5, eD=1E-4)
pg.append(p)
ro = CP.PropsSI('D', 'T', (273.15 + T), 'P', (p * 1e5),
fluid) # gustoca pri trenutnom tlaku
mi = CP.PropsSI('V', 'T', (273.15 + T), 'P', (p * 1e5),
fluid) # viskoznost pri trenutnom tlaku
dens.append(ro)
mu.append(mi)
q_rc = q * ro_sc / ro # volumni protok u busotini pri zadanoj gustoci i protoku na povrsini
v = q_rc / (np.pi * 0.25 * d**2) # brzina protjecanja m/s
Re = funcRe(ro, v, d, mi) # Reynoldsov broj
Reg.append(Re)
flow_type.append(funcReg(Re, e))
print('{0:.4g}'.format(p), zi, '{0:.4g}'.format(ro), '{0:.4g}'.format(mi),
'{0:.4g}'.format(v), '{0:.4g}'.format(q), dpf)
# Clamond, Didier, 2009. “Efficient Resolution of the Colebrook Equation.”
f = fluids.friction_factor(
Re=Re, eD=eD) # Clamondova jednadzba - bolja od Haalandove
dpf = funcdpf(f, dz, d, ro, v)
if proizvodna:
dp = ro * g * dz - ro * v * dz + dpf # - ro * v * dz ?
else:
dp = ro * g * dz + ro * v * dz - dpf
dp = dp * 1e-5
p = p - dp
if p < 0: break
h_THP = CP.PropsSI('H', 'T', (273.15 + T), 'P', (p * 1e5),
fluid) # specificna entalpija, J/kg
m_out = q * ro # maseni protok, kg/m3
THP = '{0:.4g}'.format(pg[-1]) # tlak na povrsini (izlazu), bar
def run():
# w2 components
# CdA_PRO_PFTI
# Lines leading to tank inlet, check valve, helium
# DP < 5, ignore
# CdA_PFTI_PFT
# Fuel tank diffuser section to ullage start, helium
# DP < 5, ignore
# CdA_PFT_PFTO
# Fuel tank gas/liquid line, converging section to line diameter
# CdA_PFTO_PMFVI
# Lines leading up to main fuel valve inlet
# CdA_PMFVI_PFMVO
# CdA of main fuel valve
# CdA_PMFVO_PFCI
# Lines leading to film coolant inlet branch
w2guess = w_fu * (ureg.lb / ureg.s)
D2 = (D2_OD - 2 * t2) * ureg.inch
Re2 = (4 / np.pi) * (w2guess /
(D2.to('ft') * RP1_DynamicViscosity_DEFAULT))
f2 = fl.friction_factor(Re2, eD=ABS_ROUGHNESS_SS / D2)
Tank_Diameter = 1 * ureg.ft
K_PFT_PFTO = fl.fittings.contraction_conical(Tank_Diameter.to('m'),
D2,
f2,
l=(4 * ureg.inch).to('m'))
CdA_PFT_PFTO = K_to_CdA(K_PFT_PFTO, D=D2)
K_PFTO_PMFVI = fl.K_from_f(f2, L=(5 * ureg.ft).to('in'),
D=D2) # line losses
K_PFTO_PMFVI += fl.fittings.bend_rounded(D2,
angle=90,
fd=f2,
bend_diameters=5)
K_PFTO_PMFVI += fl.fittings.bend_rounded(D2,
angle=90,
fd=f2,
bend_diameters=5)
K_PFTO_PMFVI += fl.fittings.bend_rounded(D2,
angle=90,
fd=f2,
bend_diameters=5)
CdA_PFTO_PMFVI = K_to_CdA(K_PFTO_PMFVI, D=D2)
K_PMFVI_PMFVO = fl.fittings.K_ball_valve_Crane(D1=D2 * 0.8,
D2=D2,
angle=0,
fd=f2)
CdA_PMFVI_PMFVO = K_to_CdA(K_PMFVI_PMFVO, D=D2)
K_PMFVO_PREGI = fl.K_from_f(f2, L=(3.5 * ureg.ft).to('in'), D=D2)
K_PMFVO_PREGI += fl.fittings.bend_rounded(D2,
angle=90,
fd=f2,
bend_diameters=5)
K_PMFVO_PREGI += fl.fittings.bend_rounded(D2,
angle=90,
fd=f2,
bend_diameters=5)
CdA_PMFVO_PREGI = K_to_CdA(K_PMFVO_PREGI, D=D2)
# PITCH_NOZZLE_OUTLET = CHANNEL_WIDTH_NOZZLE_OUTLET * np.sin(np.deg2rad(EXPANSION_ANGLE))
# NUMCOILS_NOZZLE = (R_NOZZLE_EXIT - (R_THROAT + R_NOZZLE_EXIT * 0.3)) / PITCH_NOZZLE_OUTLET
# PITCH_NOZZLE_OUTLET = (R_NOZZLE_EXIT - (R_THROAT + RDIFF)) / NUMCOILS_NOZZLE
# Nozzle "spiral"
THROAT_COOLING_VELOCITY = 40 * ureg.ft / ureg.s
NOZZLE_CHAMBER_COOLING_VELOCITY = 20 * ureg.ft / ureg.s
COOLING_CHANNEL_HEIGHT = 0.3 * ureg.inch
CHANNEL_WIDTH_NOZZLE = (
w2guess / (RP1_Density_DEFAULT * NOZZLE_CHAMBER_COOLING_VELOCITY *
COOLING_CHANNEL_HEIGHT)).to('in')
CHANNEL_WIDTH_THROAT = (w2guess /
(RP1_Density_DEFAULT * THROAT_COOLING_VELOCITY *
COOLING_CHANNEL_HEIGHT)).to('in')
# Spacing between each coil
CHANNEL_WIDTH_HEAD = CHANNEL_WIDTH_NOZZLE
CHAMBER_THICKNESS = 0.15 * ureg.inch
CHAMBER_PRESSURE = 300 * ureg.psi
mdot_total = (w_fu + w_ox) * ureg.lb / ureg.s
cstar = (getCstar(w_ox, w_fu) * ureg.m / ureg.s).to('ft / s')
AREA_THROAT = ((mdot_total * cstar) / CHAMBER_PRESSURE).to('in ** 2')
ID_THROAT = np.sqrt(4 * AREA_THROAT / np.pi)
EXPANSION_RATIO = 4.15
CONTRACTION_RATIO = 6
DIA_THROAT = ID_THROAT + 2 * CHAMBER_THICKNESS
R_THROAT = DIA_THROAT / 2
AREA_NOZZLE_EXIT = AREA_THROAT * EXPANSION_RATIO
DIA_NOZZLE_EXIT = np.sqrt(
4 * AREA_NOZZLE_EXIT / np.pi) + 2 * CHAMBER_THICKNESS
R_NOZZLE_EXIT = DIA_NOZZLE_EXIT / 2
# Radius where channel width is decreased in order to increase fluid velocity and provide more cooling
# In reality this is a gradual change, but for simplicity an average width will be taken with an abrupt change
R_WIDTHCHANGE = R_THROAT + (R_NOZZLE_EXIT - R_THROAT) * 0.5
AREA_CHAMBER = AREA_THROAT * CONTRACTION_RATIO
DIA_CHAMBER = np.sqrt(4 * AREA_CHAMBER / np.pi) + 2 * CHAMBER_THICKNESS
R_CHAMBER = DIA_CHAMBER / 2
DH_NOZZLE = getHydraulicDiameterRectangle(
COOLING_CHANNEL_HEIGHT,
CHANNEL_WIDTH_NOZZLE) # Hydraulic Diameter, approx
DH_THROAT = getHydraulicDiameterRectangle(COOLING_CHANNEL_HEIGHT,
CHANNEL_WIDTH_THROAT)
DH_HEAD = DH_NOZZLE
EXPANSION_ANGLE = 11
CONTRACTION_ANGLE = 45
PITCH_NOZZLE = CHANNEL_WIDTH_NOZZLE * np.cos(np.deg2rad(EXPANSION_ANGLE))
PITCH_THROAT_EXPANSION = CHANNEL_WIDTH_THROAT * np.cos(
np.deg2rad(EXPANSION_ANGLE))
PITCH_THROAT_CONTRACTION = CHANNEL_WIDTH_THROAT * np.cos(
np.deg2rad(CONTRACTION_ANGLE))
PITCH_HEAD = CHANNEL_WIDTH_HEAD
NUMCOILS_NOZZLE = (2 * ureg.inch) / PITCH_NOZZLE
NUMCOILS_THROAT_EXPANSION = (2 * ureg.inch) / PITCH_THROAT_EXPANSION
NUMCOILS_THROAT_CONTRACTION = (0.8 * ureg.inch) / PITCH_THROAT_CONTRACTION
NUMCOILS_HEAD = (5.4 * ureg.inch) / PITCH_HEAD
# Loss through diverging nozzle section
Re_NOZZLE = (4 /
np.pi) * (w2guess /
(DH_NOZZLE.to('ft') * RP1_DynamicViscosity_DEFAULT))
f_NOZZLE = fl.friction_factor(Re_NOZZLE, eD=ABS_ROUGHNESS_SS / DH_NOZZLE)
K_NOZZLE = fl.fittings.helix(DH_NOZZLE,
(R_NOZZLE_EXIT + R_WIDTHCHANGE) / 2,
PITCH_NOZZLE, NUMCOILS_NOZZLE, f_NOZZLE)
CdA_NOZZLE_REGEN = K_to_CdA(K_NOZZLE, DH_NOZZLE)
# Loss through throat regen, diverging section
Re_THROAT = (4 /
np.pi) * (w2guess /
(DH_THROAT.to('ft') * RP1_DynamicViscosity_DEFAULT))
f_THROAT = fl.friction_factor(Re_THROAT, eD=ABS_ROUGHNESS_SS / DH_THROAT)
K_THROAT_EXPANSION = fl.fittings.helix(DH_THROAT,
(R_WIDTHCHANGE + R_THROAT) / 2,
PITCH_THROAT_EXPANSION,
NUMCOILS_THROAT_EXPANSION, f_THROAT)
CdA_THROAT_EXPANSION = K_to_CdA(K_THROAT_EXPANSION, DH_THROAT)
# Loss through throat regen, contracting section
K_THROAT_CONTRACTION = fl.fittings.helix(DH_THROAT,
(R_CHAMBER + R_THROAT) / 2,
PITCH_THROAT_CONTRACTION,
NUMCOILS_THROAT_CONTRACTION,
f_THROAT)
CdA_THROAT_CONTRACTION = K_to_CdA(K_THROAT_CONTRACTION, DH_THROAT)
CdA_PREGI_PFCI = CdA_sum_series(
[CdA_NOZZLE_REGEN, CdA_THROAT_EXPANSION, CdA_THROAT_CONTRACTION])
# w3 components
# CdA_PFCI_PFM
# Regen circuit leading to fuel manifold
# CdA_PFM_PC
# CdA of fuel injector
w3guess = w2guess * ((100 - PERCENT_FFC) / 100.0)
Re_HEAD = (4 / np.pi) * (w3guess /
(DH_HEAD.to('ft') * RP1_DynamicViscosity_DEFAULT))
f3 = fl.friction_factor(Re_HEAD, eD=ABS_ROUGHNESS_SS / DH_HEAD)
K_PFCI_PFM = fl.fittings.helix(DH_HEAD, R_CHAMBER, CHANNEL_WIDTH_HEAD,
NUMCOILS_HEAD, f3)
CdA_PFCI_PFM = K_to_CdA(K_PFCI_PFM, D=DH_HEAD)
# Ares 2017-2018 INJECTOR GEOMETRIES, Dave Crisalli design
# NUM_FUEL_HOLES = 16
# DIA_FUEL_HOLES = 0.052 * ureg.inch
# NUM_FUEL_SHOWERHEAD_HOLES = 8
# DIA_FUEL_SHOWEHEAD_HOLES = 0.029 * ureg.inch
# NUM_HEAD_FFC_HOLES = 16
# DIA_HEAD_FFC_HOLES = 0.029 * ureg.inch
# Cd_PFM_PC = 0.78 # Determined empirically through waterflow data
# A_PFM_PC = np.pi / 4 * (NUM_FUEL_HOLES * DIA_FUEL_HOLES ** 2 + NUM_HEAD_FFC_HOLES * DIA_HEAD_FFC_HOLES ** 2 +
# NUM_FUEL_SHOWERHEAD_HOLES * DIA_FUEL_SHOWEHEAD_HOLES ** 2)
# CdA_PFM_PC = Cd_PFM_PC * A_PFM_PC
INJECTOR_PRESSURE_DROP = CHAMBER_PRESSURE * 0.26
Cd_PFM_PC = 0.7
A_FUEL_HOLES = ((12 * w2guess / Cd_PFM_PC) /
np.sqrt(2 * G_const * RP1_Density_DEFAULT *
INJECTOR_PRESSURE_DROP)).magnitude * ureg.inch**2
NUM_FUEL_HOLES = 150
DIA_FUEL_HOLES = np.sqrt(4 / np.pi * A_FUEL_HOLES / NUM_FUEL_HOLES)
# NUM_HEAD_FFC_HOLES = 32
# DIA_HEAD_FFC_HOLES = 0.0135 * ureg.inch
# A_HEAD_FFC_HOLES = np.pi / 4 * NUM_HEAD_FFC_HOLES * DIA_HEAD_FFC_HOLES ** 2
# CdA_HEAD_FFC_HOLES = Cd_PFM_PC * A_HEAD_FFC_HOLES
CdA_FUEL_HOLES = Cd_PFM_PC * A_FUEL_HOLES
CdA_PFM_PC = CdA_FUEL_HOLES
# w4 components
# CdA_PFCI_PC
# CdA of chamber holes
w4guess = w2guess * (PERCENT_FFC / 100.0)
Cd_PFCI_PC = 0.7
THROAT_FFC_VELOCITY = 52 * ureg.ft / ureg.s
THROAT_FFC_DP = (144 * THROAT_FFC_VELOCITY.magnitude**2) / (
2 * G_const * RP1_Density_DEFAULT.magnitude)
# D4 = 0.25 * ureg.inch
# Re4 = (4 / np.pi) * (w4guess / (DH_THROAT.to('ft') * RP1_DynamicViscosity_DEFAULT) )
# f4 = fl.friction_factor(Re4, eD=ABS_ROUGHNESS_SS/DH_THROAT)
A_THROAT_FFC_HOLES = ((12 * w4guess / Cd_PFCI_PC) /
np.sqrt(2 * G_const * RP1_Density_DEFAULT *
THROAT_FFC_DP)).magnitude * ureg.inch**2
NUM_THROAT_FFC_HOLES = 24
DIA_FUEL_HOLES = np.sqrt(4 / np.pi * A_THROAT_FFC_HOLES /
NUM_THROAT_FFC_HOLES)
CdA_PFCI_PC = Cd_PFCI_PC * A_THROAT_FFC_HOLES
# w5 components
# CdA_PRO_POTI
# Lines leading to tank inlet, check valve
# CdA_POTI_POT
# Diffuser tank section, portion of tank filled with gas
# CdA_POT_POTO
# Liquid oxygen in tank to converging duct on outlet
# CdA_POTO_PMOVI
# Lines leading up to main ox valve
# CdA_PMOVI_PMOVO
# CdA of main oxidizer valve
# CdA_PMOVO_POM
# CdA of lines leading to fuel manifold
# CdA_POM_PC
# CdA of ox injector
w5guess = w_ox * (ureg.lb / ureg.s)
D5 = (D5_OD - 2 * t5) * ureg.inch
Re5 = (4 / np.pi) * (w5guess /
(D5.to('ft') * LOX_DynamicViscosity_DEFAULT))
f5 = fl.friction_factor(Re5, eD=ABS_ROUGHNESS_SS / D5)
Tank_Diameter = 1 * ureg.ft
K_POT_POTO = fl.fittings.contraction_conical(Tank_Diameter.to('m'),
D2,
f2,
l=4 * ureg.inch)
CdA_POT_POTO = K_to_CdA(K_POT_POTO, D=D2)
K_POTO_PMOVI = fl.K_from_f(f5, L=(5 * ureg.ft).to('in'),
D=D5) # line losses
K_POTO_PMOVI += fl.fittings.bend_rounded(D5,
angle=90,
fd=f5,
bend_diameters=5)
K_POTO_PMOVI += fl.fittings.bend_rounded(D5,
angle=90,
fd=f5,
bend_diameters=5)
CdA_POTO_PMOVI = K_to_CdA(K_POTO_PMOVI, D=D5)
K_PMOVI_PMOVO = fl.fittings.K_ball_valve_Crane(D1=D5 * 0.8,
D2=D5,
angle=0,
fd=f5)
CdA_PMOVI_PMOVO = K_to_CdA(K_PMOVI_PMOVO, D=D5)
K_PMOVO_POM = fl.K_from_f(f5, L=(3 * ureg.ft).to('in'), D=D5)
CdA_PMOVO_POM = K_to_CdA(K_PMOVO_POM, D=D5)
# ARES 2017-2018 INJECTOR GEOMETRIES
# NUM_OX_HOLES = 16
# DIA_OX_HOLES = 0.070 * ureg.inch
# Cd_POM_PC = 0.685 # Empirical waterflow testing of injector ares 2017-2018
# CdA_POM_PC = NUM_OX_HOLES * np.pi/4 * DIA_OX_HOLES ** 2 * Cd_POM_PC
# BPL 2018-2019 INJECTOR GEOMETRIES
Cd_POM_PC = 0.7
A_OX_HOLES = ((12 * w5guess / Cd_POM_PC) /
np.sqrt(2 * G_const * LOX_Density_DEFAULT *
INJECTOR_PRESSURE_DROP)).magnitude * ureg.inch**2
NUM_OX_HOLES = 150
DIA_OX_HOLES = np.sqrt(4 / np.pi * A_OX_HOLES / NUM_OX_HOLES)
CdA_POM_PC = Cd_POM_PC * A_OX_HOLES
# Get leg alpha CdA's
# Recall, alpha = (12 / CdA ) ** 2 * 1 / (2*g*rho)
a2cda = CdA_sum_series([
CdA_PFT_PFTO, CdA_PFTO_PMFVI, CdA_PMFVI_PMFVO, CdA_PMFVO_PREGI,
CdA_PREGI_PFCI
])
a3cda = CdA_sum_series([CdA_PFCI_PFM, CdA_PFM_PC])
a4cda = CdA_PFCI_PC
CdA_PFCI_PC_Total = a3cda + a4cda
CdA_PREGI_PC = CdA_sum_series([CdA_PFCI_PC_Total, CdA_PREGI_PFCI])
a5cda = CdA_sum_series([
CdA_POT_POTO, CdA_POTO_PMOVI, CdA_PMOVI_PMOVO, CdA_PMOVO_POM,
CdA_POM_PC
])
a2 = (12 / a2cda)**2 * 1 / (2 * G_const * RP1_Density_DEFAULT)
a3 = (12 / a3cda)**2 * 1 / (2 * G_const * RP1_Density_DEFAULT)
a4 = (12 / a4cda)**2 * 1 / (2 * G_const * RP1_Density_DEFAULT)
a5 = (12 / a5cda)**2 * 1 / (2 * G_const * LOX_Density_DEFAULT)
# Estimated DP's (based on flow rate guesses/targets)
print('Target DP\'s based on CdA, flow rate')
DP_POTO_PMOVIg = CdA_to_DP(CdA_POTO_PMOVI, w5guess, LOX_Density_DEFAULT)
DP_PMOVI_PMOVOg = CdA_to_DP(CdA_PMOVI_PMOVO, w5guess, LOX_Density_DEFAULT)
DP_PMOVO_POMg = CdA_to_DP(CdA_PMOVO_POM, w5guess, LOX_Density_DEFAULT)
DP_POM_PCg = CdA_to_DP(CdA_POM_PC, w5guess, LOX_Density_DEFAULT)
DP_OX_LINES = DP_POTO_PMOVIg + DP_PMOVI_PMOVOg + DP_PMOVO_POMg
DP_PFTO_PMFVIg = CdA_to_DP(CdA_PFTO_PMFVI, w2guess, RP1_Density_DEFAULT)
DP_PMFVI_PMFVOg = CdA_to_DP(CdA_PMFVI_PMFVO, w2guess, RP1_Density_DEFAULT)
DP_PMFVO_PREGIg = CdA_to_DP(CdA_PMFVO_PREGI, w2guess, RP1_Density_DEFAULT)
DP_PREGI_PFCIg = CdA_to_DP(CdA_PREGI_PFCI, w2guess, RP1_Density_DEFAULT)
DP_PFCI_PCg = CdA_to_DP(CdA_PFCI_PC, w4guess, RP1_Density_DEFAULT)
DP_PFCI_PFMg = CdA_to_DP(CdA_PFCI_PFM, w3guess, RP1_Density_DEFAULT)
DP_PFM_PCg = CdA_to_DP(CdA_PFM_PC, w3guess, RP1_Density_DEFAULT)
DP_FUEL_LINES = DP_PFTO_PMFVIg + DP_PMFVI_PMFVOg + DP_PMFVO_PREGIg
w1guess = w2guess + w5guess
PCguess = 300 * ureg.psi
guessarr = (w1guess.magnitude, w2guess.magnitude, w3guess.magnitude,
w4guess.magnitude, w5guess.magnitude, PCguess.magnitude)
PORO_guess = PCguess.magnitude + (a5 * w5guess**2).magnitude
PFRO_guess = PCguess.magnitude + (a3 * w3guess**2).magnitude + (
a2 * w2guess**2).magnitude
PORO = 458 * ureg.psi
PFRO = 562 * ureg.psi
DIA_THROAT = ID_THROAT
At = np.pi / 4 * DIA_THROAT**2
# cstar = (1805 * ureg.m / ureg.s).to('ft / s')
cstarEffciency = 0.95
ct = 1.4 # thrust coefficient
data = (a2.magnitude, a3.magnitude, a4.magnitude, a5.magnitude,
PORO.magnitude, PFRO.magnitude, At.magnitude, cstarEffciency)
sol = sp.fsolve(equations, guessarr, args=data)
w1, w2, w3, w4, w5, PC = sol
w3_main = w3 * CdA_FUEL_HOLES / CdA_PFM_PC
# w3_head_ffc = w3 * CdA_HEAD_FFC_HOLES / CdA_PFM_PC
DP_PREGI_PFM = CdA_to_DP(CdA_PREGI_PFCI, w2,
rho=RP1_Density_DEFAULT) + CdA_to_DP(
CdA_PFCI_PFM, w3, rho=RP1_Density_DEFAULT)
DP_PFM_PC = CdA_to_DP(CdA_PFM_PC, w3, rho=RP1_Density_DEFAULT)
DP_POM_PC = CdA_to_DP(CdA_POM_PC, w5, rho=LOX_Density_DEFAULT)
print('Total mdot: ' + str(w1 * ureg.lb / ureg.s))
print('Total fuel mdot: ' + str(w2 * ureg.lb / ureg.s))
print('Total Ox mdot: ' + str(w5 * ureg.lb / ureg.s))
print('Mixture Ratio: ' + str(w5 / w2))
# print('Total throat FFC mdot: '+str(w4 * ureg.lb / ureg.s))
print('Percent throat FFC: ' + str(w4 / w2 * 100))
# print('Percent head FFC: '+str(w3_head_ffc / w2 * 100))
print('Regen pressure drop: ' + str(DP_PREGI_PFM))
print('Fuel Injector Pressure Drop: ' + str(DP_PFM_PC))
print('Ox Injector Pressure Drop: ' + str(DP_POM_PC))
print('Chamber Pressure: ' + str(PC * ureg.psi))
print('Cstar: ' + str(getCstar(w5, w2) * ureg.m / ureg.s))
print('Thrust: ' + str((PC * ureg.psi * At * ct).to('lbf')))
print('Done!')