from rocketprops.line_supt import calc_line_id_dp, calc_line_vel_dp
from rocketprops.rocket_prop import get_prop
pObj = get_prop('hydrazine')
ID, deltaP = calc_line_id_dp( pObj, TdegR=530.0, Ppsia=240.0,
wdotPPS=0.5, velFPS=13,
roughness=5.0E-6, Kfactors=5.0, len_inches=50.0)
print( 'Inside Diam=%g inches, Pressure Drop =%g psid'%(ID, deltaP) )
vel, dp = calc_line_vel_dp( pObj, TdegR=530.0, Ppsia=240.0,
wdotPPS=0.5, IDinches=ID,
roughness=5.0E-6, Kfactors=5.0, len_inches=50.0)
print( 'Velocity = %g ft/sec, Pressure Drop =%g psid'%(vel, deltaP) )
from rocketprops.rocket_prop import get_prop
from rocketprops.injector_supt import calc_inj_velocity, calc_orifice_flow_rate
"""
Calculate the injection velocity of an injector orifice and its mass flow rate
"""
pObj = get_prop('N2O4')
ft_per_sec = calc_inj_velocity(pObj, dPpsia=50.0, TdegR=530.0, Ppsia=1000.0)
print('velocity =', ft_per_sec, 'ft/s')
wdot = calc_orifice_flow_rate(pObj,
CdOrf=0.75,
DiamInches=0.01,
dPpsia=50.0,
TdegR=530.0,
Ppsia=1000.0)
print('Orifice flow rate =', wdot, 'lbm/sec')
import matplotlib.pyplot as plt
from rocketprops.rocket_prop import get_prop
from engcoolprop.ec_fluid import EC_Fluid
from rocketprops.unit_conv_data import get_value
name = 'Oxygen'
name = 'Propane'
#name = 'Methane'
#name = 'Methanol'
#name = 'Ethanol'
#name = 'Ammonia'
ec = EC_Fluid(name)
p = get_prop(name)
Tmin, Tmax = p.T_data_range()
Tmin += 5
Tmax = min( Tmax, ec.Tc ) - 5.0
print( 'p.Tc=%g, ec.Tc=%g'%(p.Tc, ec.Tc) )
fig = plt.figure()
COLORL = ['g','c','b','orange','m','r']
i = 0
errLL = []
plt.title( p.pname )
for P in [100, 200, 500, 1000, 2000]:
tL = []
sg_rpL = []
sg_ecL = []
errL = []
terrL = []
"""
This example demonstrates the proper use of project: rocketprops
"""
import sys
import os
sys.path.insert(0, os.path.abspath(
"../../")) # needed to find rocketprops development version
from rocketprops.rocket_prop import get_prop
p = get_prop('c3h8')
p.summ_print()
p.plot_sat_props(save_figures=True)
from rocketprops.rocket_prop import get_prop
from rocketprops.valve_supt import cv_valve_dp, kv_valve_dp
"""
Calculate the pressure drop across an MMH valve with given mass flow rate
"""
pObj = get_prop( 'MMH' )
# Imperial valve flow coefficient, Cv
dp = cv_valve_dp( pObj, Cv=1.0, wdotPPS=0.5, TdegR=530.0, Ppsia=1000.0)
print('Cv = 1.0 deltaP = %g psid'%dp)
# Metric valve flow coefficient, Kv
Kv = 1.0 / 1.1560992283526375 # Conversion factor for Cv to Kv
dp = kv_valve_dp( pObj, Kv=Kv, wdotPPS=0.5, TdegR=530.0, Ppsia=1000.0)
print('Kv = 1.0/convFact deltaP = %g psid'%dp)
from rocketprops.tank_supt import calc_tank_volume
from rocketprops.rocket_prop import get_prop
"""
Calculate the required volume of a Hydrazine (N2H4) tank.
Assume:
required usable propellant is 50 kg
vehicle max operating/storage/transport temperature is 50 deg C.
minimum ullage volume is 3%.
expulsion efficiency = 98%.
"""
pObj = get_prop('N2H4')
cc_Total, kg_loaded, kg_residual = calc_tank_volume(pObj,
kg_expelled=50.0,
TmaxC=50.0,
expPcent=98.0,
ullPcent=3.0)
print('cc_Total = %g cc' % cc_Total)
print('loaded propellant mass = %g kg' % kg_loaded)
print('residual propellant mass = %g kg' % kg_residual)
def __init__(self, coreObj, # CoreStream object
Tox=None, Tfuel=None, elemEm=0.8,
fdPinjOx=0.25, fdPinjFuel=0.25, dpOxInp=None, dpFuelInp=None,
setNelementsBy='acoustics', # can be "acoustics", "elem_density", "input"
elemDensInp=5, NelementsInp=100,
OxOrfPerEl=1.0, FuelOrfPerEl=1.0,
lolFuelElem=False,
setAcousticFreqBy='mode', # can be "mode" or "freq"
desAcousMode='3T', desFreqInp=5000,
CdOxOrf=0.75, CdFuelOrf=0.75, dropCorrOx=0.33, dropCorrFuel=0.33,
DorfMin=0.008,
LfanOvDorfOx=20.0, LfanOvDorfFuel=20.0):
"""
Injector object holds basic information about the injector.
Injector design features are calculated
including chamber losses due to the injector, Em, Mix and Vap.
"""
self.coreObj = coreObj
self.geomObj = coreObj.geomObj
# build propellant objects
self.oxProp = get_prop( self.coreObj.oxName )
self.fuelProp = get_prop( self.coreObj.fuelName )
self.TminOx, self.TmaxOx = self.oxProp.T_data_range()
self.TminFuel, self.TmaxFuel = self.fuelProp.T_data_range()
self.Tox_warning = ''
self.Tfuel_warning = ''
if Tox is None:
Tox = min(530.0, self.oxProp.Tnbp)
else:
Tox, self.Tox_warning = temperature_clamp(Tox, 'Tox', self.TminOx, self.TmaxOx)
self.Tox = Tox
if Tfuel is None:
Tfuel = min(530.0, self.fuelProp.Tnbp)
else:
Tfuel,self.Tfuel_warning = temperature_clamp(Tfuel, 'Tfuel', self.TminFuel, self.TmaxFuel)
self.Tfuel = Tfuel
self.elemEm = min(1.0, elemEm) # intra-element mixing parameter for injector
self.fdPinjOx = fdPinjOx
self.fdPinjFuel = fdPinjFuel
self.dpOxInp = dpOxInp
self.dpFuelInp = dpFuelInp
self.setNelementsBy = setNelementsBy.lower() # just in case user screw up.
self.used_Nelem_criteria = self.setNelementsBy # assume for now that intention is satisfied
self.elemDensInp = elemDensInp
self.NelementsInp = NelementsInp
self.OxOrfPerEl = OxOrfPerEl
self.FuelOrfPerEl = FuelOrfPerEl
self.lolFuelElem = lolFuelElem
if lolFuelElem:
self.strouhal_mult = 0.1 # LOL element uses 0.1 strouhal multiplier
else:
self.strouhal_mult = 0.2 # unlike element uses 0.2 strouhal multiplier
self.desAcousMode = desAcousMode
if desAcousMode in modeSvnD:
self.desAcousMult = modeSvnD[ desAcousMode ]
else:
self.desAcousMult = float( desAcousMode ) # let it raise exception if not a float
self.desFreqInp = desFreqInp
self.setAcousticFreqBy = setAcousticFreqBy.lower() # can be "mode" or "freq"
self.CdOxOrf = CdOxOrf
self.CdFuelOrf = CdFuelOrf
self.dropCorrOx = dropCorrOx
self.dropCorrFuel = dropCorrFuel
self.DorfMin = DorfMin
self.LfanOvDorfOx = LfanOvDorfOx
self.LfanOvDorfFuel = LfanOvDorfFuel
# get oxidizer propellant properties
self.sgOx = self.oxProp.SG_compressed( Tox, self.coreObj.Pc ) # g/ml
self.dHvapOx = self.oxProp.HvapAtTdegR( Tox ) # BTU/lbm
self.surfOx = self.oxProp.SurfAtTdegR( Tox ) # lbf/in
self.viscOx = self.oxProp.ViscAtTdegR( Tox ) # poise
self.viscOx = get_value( self.viscOx, 'poise', 'lbm/s/ft')
self.MolWtOx = self.oxProp.MolWt
#print('sgOx=',self.sgOx)
# get fuel propellant properties
self.sgFuel = self.fuelProp.SG_compressed( Tfuel, self.coreObj.Pc ) # g/ml
self.dHvapFuel = self.fuelProp.HvapAtTdegR( Tfuel ) # BTU/lbm
self.surfFuel = self.fuelProp.SurfAtTdegR( Tfuel ) # lbf/in
self.viscFuel = self.fuelProp.ViscAtTdegR( Tfuel ) # poise
self.viscFuel = get_value( self.viscFuel, 'poise', 'lbm/s/ft')
self.MolWtFuel = self.fuelProp.MolWt
#print('sgFuel=',self.sgFuel)
# --------- start vaporization calcs --------
self.rhoOx = rho = get_value( self.sgOx, 'SG', 'lbm/in**3' )
self.rhoFuel = rho = get_value( self.sgFuel, 'SG', 'lbm/in**3' )
self.calc_element_attr() # e.g. Nelements, injection velocities, elements diam, etc.
#self.evaluate()
# get input descriptions and units from doc string
self.inp_descD, self.inp_unitsD, self.is_inputD = get_desc_and_units( self.__doc__ )
def setUp(self):
unittest.TestCase.setUp(self)
self.myclass = get_prop('N2O4')
