# ideal-shock-test.py
#
# $ prep-gas ideal-air.inp ideal-air-gas-model.lua
# $ python3 ideal-shock-test.py
#
# PJ, 2019-11-28
#
import math
from eilmer.gas import GasModel, GasState, GasFlow
gmodel = GasModel('ideal-air-gas-model.lua')
state1 = GasState(gmodel)
state1.p = 125.0e3 # Pa
state1.T = 300.0 # K
state1.update_thermo_from_pT()
state1.update_sound_speed()
print("state1: %s" % state1)
print("normal shock (in ideal gas), given shock speed")
vs = 2414.0
state2 = GasState(gmodel)
flow = GasFlow(gmodel)
v2, vg = flow.ideal_shock(state1, vs, state2)
print("v2=%g vg=%g" % (v2, vg))
print("state2: %s" % state2)
#
# PJ, 2019-12-01
#
import math
def approxEqual(a, b):
result = math.isclose(a, b, rel_tol=1.0e-2, abs_tol=1.0e-5)
# print("a=",a, "b=",b, "rel=",(a-b)/b, "abs=",a-b, "result=",result)
return result
from eilmer.gas import GasModel, GasState, GasFlow
m1 = 1.5
print("Conical-shock demo for m1=%g" % m1)
gmodel = GasModel('cea-air13species-gas-model.lua')
state1 = GasState(gmodel)
state1.p = 100.0e3 # Pa
state1.T = 300.0 # K ideal air, not high T
state1.update_thermo_from_pT()
state1.update_sound_speed()
print("state1: %s" % state1)
v1 = m1*state1.a
print("v1=%g" % v1)
beta = 45.0 * math.pi/180.0
print(" given beta(degrees)=%g" % (beta*180/math.pi))
state_c = GasState(gmodel)
flow = GasFlow(gmodel)
theta_c, v_c = flow.theta_cone(state1, v1, beta, state_c)
print(" theta_c=%g degrees" % (theta_c*180/math.pi))
print(" v_c=%g" % (v_c))
print(" state_c: %s" % state_c)
# of air (as a mixture of N2 and O2) from 200 -- 20000 K.
#
# Author: Peter J. and Rowan J. Gollan
# Date: 2019-11-21
#
# To run this script:
# $ prep-gas thermally-perfect-N2-O2.inp thermally-perfect-N2-O2.lua
# $ python3 transport-properties-for-air.py
#
from eilmer.gas import GasModel, GasState
gasModelFile = 'thermally-perfect-N2-O2.lua'
gmodel = GasModel(gasModelFile)
gs = GasState(gmodel)
gs.p = 1.0e5 # Pa
gs.massf = {"N2":0.78, "O2":0.22} # approximation for the composition of air
outputFile = 'trans-props-air.dat'
print("Opening file for writing: %s" % outputFile)
f = open(outputFile, "w")
f.write("# 1:T[K] 2:mu[Pa.s] 3:k[W/(m.K)]\n")
lowT = 200.0
dT = 100.0
for i in range(199):
gs.T = dT*i + lowT
gs.update_thermo_from_pT()
gs.update_trans_coeffs()
f.write(" %12.6e %12.6e %12.6e\n" % (gs.T, gs.mu, gs.k))
# $ python3 poshax.py
#
#------------------------------------------------------------------
from eilmer.gas import GasModel, GasState, GasFlow, ThermochemicalReactor
debug = False
print("Initialise a gas model.")
print("air 7 species Gupta-et-al reactions")
gmodel = GasModel("air-7sp-gas-model.lua")
nsp = gmodel.n_species
nmodes = gmodel.n_modes
if debug: print("nsp=", nsp, " nmodes=", nmodes, " gmodel=", gmodel)
reactor = ThermochemicalReactor(gmodel, "air-7sp-chemistry.lua")
# The example here matches the case discussed on page 63 of the thesis.
state1 = GasState(gmodel)
state1.p = 133.3 # Pa
state1.T = 300.0 # degree K
state1.massf = {"N2": 0.78, "O2": 0.22}
print("Free stream conditions, before the shock.")
state1.update_thermo_from_pT()
state1.update_sound_speed()
print(" state1: %s" % state1)
mach1 = 12.28
v1 = mach1 * state1.a
print("mach1:", mach1, "v1:", v1)
print("Stationary normal shock with chemically-frozen gas.")
flow = GasFlow(gmodel)
state2 = GasState(gmodel)
v2, vg = flow.normal_shock(state1, v1, state2)
print(" v2=", v2, "vg=", vg)
# Step through a steady isentropic expansion,
# from stagnation condition to sonic condition.
#
# $ prep-gas ideal-air.inp ideal-air-gas-model.lua
# $ python3 isentropic-air-expansion.py
#
# Python port, PJ, 2019-11-21
#
import math
from eilmer.gas import GasModel, GasState
gmodel = GasModel('ideal-air-gas-model.lua')
gs = GasState(gmodel)
gs.p = 500e3 # Pa
gs.T = 300.0 # K
gs.update_thermo_from_pT()
# Compute enthalpy and entropy at stagnation conditions
h0 = gs.enthalpy
s0 = gs.entropy
# Set up for stepping process
dp = 1.0 # Pa, use 1 Pa as pressure step size
gs.p = gs.p - dp
mach_tgt = 1.0
# Begin stepping until Mach = mach_tgt
while True:
gs.update_thermo_from_ps(s0)
h1 = gs.enthalpy
v1 = math.sqrt(2*(h0 - h1))
m1 = v1/gs.a
if m1 >= mach_tgt:
print("Stopping at Mach=%g" % m1)
#------------------------------------------------------------------
# Start the main script...
debug = False
print("# Reacting pipe flow -- Bittker-Scullin test case 3.")
print(sample_header)
# Gas model setup
gmodel = GasModel("h2-o2-n2-9sp.lua")
nsp = gmodel.n_species
nmodes = gmodel.n_modes
if debug: print("nsp=", nsp, " nmodes=", nmodes, " gmodel=", gmodel)
print("# Gas properties at the start of the pipe.")
gas0 = GasState(gmodel)
gas0.p = 96.87e3 # Pa
x = 0.0 # m (inlet of pipe)
v = 4551.73 # m/s
gas0.T = 1559.0 # degree K
gas0.molef = {"O2": 0.1480, "N2": 0.5562, "H2": 0.2958}
gas0.update_thermo_from_pT()
dt_suggest = 1.0e-8 # suggested starting time-step for chemistry updater
print(sample_data(x, v, gas0, dt_suggest))
print("# Start reactions...")
reactor = ThermochemicalReactor(gmodel, "h2-o2-n2-9sp-18r.lua")
t = 0 # time is in seconds
t_final = 22.0e-6
t_inc = 0.05e-6
nsteps = int(t_final / t_inc)
for j in range(1, nsteps + 1):
# the gas-model Lua file is visible, as given by the path below.
#
# PJ 2019-07-24 direct use of FFI
# 2019-07-25 using Pythonic wrapper
#
from eilmer.gas import GasModel, GasState
gmodel = GasModel("ideal-air-gas-model.lua")
print("gmodel=", gmodel)
print("n_species=", gmodel.n_species, ", n_modes=", gmodel.n_modes)
print("species_names=", gmodel.species_names)
print("mol_masses=", gmodel.mol_masses)
gs = GasState(gmodel)
print("freshly minted gs=", gs)
gs.rho=1.1; gs.p=1.0e5; gs.T=300.0; gs.u=1.44e6; gs.massf=[1.0]
print("after setting some values")
print(" gs.rho=%g p=%g T=%g u=%g massf=%s a=%g k=%g mu=%g" %
(gs.rho, gs.p, gs.T, gs.u, gs.massf, gs.a, gs.k, gs.mu))
gmodel.update_thermo_from_pT(gs) # the way that we do the update in D
gmodel.update_sound_speed(gs) # not necessary from Python but is available
gmodel.update_trans_coeffs(gs)
print("after update thermo from pT")
print(" gs.rho=%g p=%g T=%g u=%g massf=%s a=%g k=%g mu=%g" %
(gs.rho, gs.p, gs.T, gs.u, gs.massf, gs.a, gs.k, gs.mu))
gs.p=3000.0; gs.T=99.0; gs.massf={'air':1.0}
gs.update_thermo_from_rhou() # update another way
gs.update_trans_coeffs()
print("after update thermo from rhou")
print(" gs.rho=%g p=%g T=%g u=%g massf=%s a=%g k=%g mu=%g" %
(gs.rho, gs.p, gs.T, gs.u, gs.massf, gs.a, gs.k, gs.mu))
#------------------------------------------------------------------
# Start the main script...
debug = False
print("# Reacting nozzle flow.")
print(sample_header)
# Gas model setup
gmodel = GasModel("h2-o2-n2-5sp.lua")
nsp = gmodel.n_species
nmodes = gmodel.n_modes
if debug: print("nsp=", nsp, " nmodes=", nmodes, " gmodel=", gmodel)
print("# Gas properties at the start of the pipe.")
gas0 = GasState(gmodel)
gas0.p = 81.0e3 # Pa
x = 0.0 # m (inlet of duct)
area = duct_area(x)
v = 1230.0 # m/s
gas0.T = 1900.0 # degree K
gas0.molef = {"O2":0.1865, "N2":0.7016, "H2":0.1119}
gas0.update_thermo_from_pT()
dt_suggest = 1.0e-12 # suggested starting time-step for chemistry
print(sample_data(x, area, v, gas0, dt_suggest))
if debug:
print("# species=", gmodel.species_names)
print("# massf=", gas0.massf)
print("# Start reactions...")
reactor = ThermochemicalReactor(gmodel, "h2-o2-n2-5sp-2r.lua")