cleaned up code, ran all SSME.py altitudes

chinahg · Oct 27, 2022 · 46059bc · 46059bc
1 parent 7b5a929
commit 46059bc
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Showing 41 changed files with 147 additions and 199 deletions.
diff --git a/SSME.py b/SSME.py
@@ -101,13 +101,13 @@
 
     if h >= 25000:
         T_atm = (-131.21 + 0.00299*h) + 273.14 #[K]
-        P_atm = (2.488 * ((T_atm)/ 216.6)**-11.388)*1000 #[Pa]
+        P_atm = (2.488 * ((T_atm)/ 216.6)**(-11.388))*1000 #[Pa]
         ambient_T = T_atm
         ambient_P = P_atm
 
     elif 11000 < h < 25000:
         T_atm = -56.46 + 273.14 #[K]
-        P_atm = (22.65*10**(1.73-0.000157*h))*1000
+        P_atm = (22.65*math.exp(1.73-0.000157*h))*1000
         ambient_T = T_atm
         ambient_P = P_atm
 
@@ -123,7 +123,6 @@
     F = 2188080 #[N] thrust at 104.5% RPL
     P_e = 13798.5 #[Pa] exit pressure of nozzle
     u_e = (F-((P_e-ambient_P)*A_exit))/(mdot_f+mdot_ox)
-    print(u_e)
 
     #Calculate composition of O2, and N2
     X_N2 = 0.78084
@@ -191,7 +190,6 @@
     mdot_Noz = mdot_f+mdot_ox
 
     L_Noz = (math.sqrt(1/3.1415 *math.sqrt(A_throat*Area_ratio)) - (1/3.1415 *math.sqrt(A_throat)))**2 #[m]
-    print(L_Noz)
     #Call nozzle function
     Noz_states = nozzle(T_Noz1, P_Noz1, comp_Noz1, A_throat, A_exit, L_Noz, mdot_ox, mdot_f)
     n = len(Noz_states.T)-1
@@ -238,7 +236,6 @@
 
     u = results_u[1] #velocity at exit of nozzle (m/s)
     gamma = 1.1
-    print(u)
     P1 = P_e #TODO Noz_states.P[n] PLACEHOLDER, need design exit pressure or design alt
     T1 = Noz_states.T[n]
     M1 = u/math.sqrt(gamma*P1/Noz_states.density[n])

diff --git a/combustion_chamber.py b/combustion_chamber.py
@@ -2,7 +2,6 @@
 import os
 
 sys.path.insert(0,"/home/chinahg/GCresearch/cantera/build/python")
-#print(sys.path)
 
 import cantera as ct
 ct.add_directory('/user/chinahg')
@@ -23,7 +22,6 @@ def combustion_chamber(P_CC0, V_CC, mdot_ox, mdot_f):
     gasExhaust = ct.Solution('h2o2.yaml')
     gasExhaust.TPY = 300, P_CC0, 'O2: 6, H2:1'
     gasExhaust.equilibrate('HP')
-    #print(gasExhaust.report())
 
     gasFuel = ct.Solution('h2o2.yaml') #ct.Hydrogen()
     gasFuel.TPX = 20.15, 227527, 'H2:1' #https://science.ksc.nasa.gov/shuttle/technology/sts-newsref/et.html#:~:text=LIQUID%20HYDROGEN%20TANK,-The%20liquid%20hydrogen&text=Its%20operating%20pressure%20range%20is,to%20the%20left%20aft%20umbilical.
@@ -70,6 +68,4 @@ def combustion_chamber(P_CC0, V_CC, mdot_ox, mdot_f):
 
     A = 0.159 #CC cross sectional area
 
-    #print("\nFinal CC Composition: ", gasExhaust.report(),"\n", u)
-
     return(state)
diff --git a/nozzle.py b/nozzle.py
@@ -98,10 +98,6 @@ def nozzle(T_Noz1, P_Noz1, comp_Noz1, A_throat, A_exit, L_Noz, mdot_ox, mdot_f):
     P_throat = P_t*(2*gamma-1)**(-gamma/(gamma-1))
     T_throat = T_t*(1/(2*gamma-1))
 
-    print("\nMACH NUMBER AT NOZZLE INLET: ", M_CC)
-    #print("\nTHROAT TEMPERATURE: ", T_throat)
-    #print("\nTHROAT PRESSURE: ", P_throat)
-
     #Call diverging section, return final gas state (end of nozzle)
     states_final = nozzle_div(T_throat, P_throat, comp_Noz1, A_throat, A_exit, L_Noz, mdot_ox,mdot_f)
     return(states_final) 
@@ -155,6 +151,5 @@ def nozzle_div(T_Noz1, P_Noz1, comp_Noz1, A_throat, A_exit, L_Noz, mdot_ox, mdot
         states.append(gas.state, x=solver.t)
 
         i = i+1
-        #print(i, solver.t, gas.report())
 
     return(states)
diff --git a/plot_data.h5 b/plot_data.h5
diff --git a/rockettests/16000m/16000_altitude.yaml b/rockettests/16000m/16000_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 3741.6934729887184
+  - 10362.151115706554
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1682.1653588139836
+  - 1845.3774305531829
 - Shocks Exit Pressure [Pa]:
-  - 3741.6934729887184
+  - 10362.151115706554
 - Shocks Exit Velocity [m/s]:
-  - 4609.12531520912
+  - 4625.755965383679
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/16250m/16250_altitude.yaml b/rockettests/16250m/16250_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 3418.3632146588047
+  - 9963.315043672133
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1668.4012378582238
+  - 1838.804521998011
 - Shocks Exit Pressure [Pa]:
-  - 3418.3632146588056
+  - 9963.315043672132
 - Shocks Exit Velocity [m/s]:
-  - 4608.313106641779
+  - 4624.754085521447
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/16500m/16500_altitude.yaml b/rockettests/16500m/16500_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 3122.972833474462
+  - 9579.830051792753
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1654.7497402094962
+  - 1832.2550249824837
 - Shocks Exit Pressure [Pa]:
-  - 3122.9728334744623
+  - 9579.830051792753
 - Shocks Exit Velocity [m/s]:
-  - 4607.571083301473
+  - 4623.790767713024
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/16750m/16750_altitude.yaml b/rockettests/16750m/16750_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 2853.1079660570754
+  - 9211.10528162192
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1641.209944340787
+  - 1825.7288561188311
 - Shocks Exit Pressure [Pa]:
-  - 2853.107966057075
+  - 9211.10528162192
 - Shocks Exit Velocity [m/s]:
-  - 4606.893180285303
+  - 4622.864527716587
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/17000m/17000_altitude.yaml b/rockettests/17000m/17000_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 2606.5628809591462
+  - 8856.572616676596
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1627.7809362653682
+  - 1819.2259323162943
 - Shocks Exit Pressure [Pa]:
-  - 2606.562880959146
+  - 8856.572616676598
 - Shocks Exit Velocity [m/s]:
-  - 4606.273856775692
+  - 4621.973938418331
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/17250m/17250_altitude.yaml b/rockettests/17250m/17250_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 2381.322450192244
+  - 8515.685807105872
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1614.4618094751027
+  - 1812.7461707800717
 - Shocks Exit Pressure [Pa]:
-  - 2381.3224501922446
+  - 8515.685807105872
 - Shocks Exit Velocity [m/s]:
-  - 4605.708050752694
+  - 4621.117627633633
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/17500m/17500_altitude.yaml b/rockettests/17500m/17500_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 2175.5456786459445
+  - 8187.9196280508995
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1601.2516648792484
+  - 1806.2894890102593
 - Shocks Exit Pressure [Pa]:
-  - 2175.5456786459445
+  - 8187.9196280508995
 - Shocks Exit Velocity [m/s]:
-  - 4605.191137619748
+  - 4620.294275992843
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/17750m/17750_altitude.yaml b/rockettests/17750m/17750_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 1987.5506567760058
+  - 7872.769070399271
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1588.1496107437683
+  - 1799.8558048008053
 - Shocks Exit Pressure [Pa]:
-  - 1987.5506567760056
+  - 7872.769070399273
 - Shocks Exit Velocity [m/s]:
-  - 4604.718892404689
+  - 4619.502614908449
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/18000m/18000_altitude.yaml b/rockettests/18000m/18000_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 1815.8008135730927
+  - 7569.748562687052
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1575.154762631136
+  - 1793.4450362384607
 - Shocks Exit Pressure [Pa]:
-  - 1815.8008135730931
+  - 7569.748562687054
 - Shocks Exit Velocity [m/s]:
-  - 4604.287455227081
+  - 4618.74142462049
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/18250m/18250_altitude.yaml b/rockettests/18250m/18250_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 1658.8923574511375
+  - 7278.391222949545
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1562.2662433406292
+  - 1787.0571017017364
 - Shocks Exit Pressure [Pa]:
-  - 1658.8923574511375
+  - 7278.391222949545
 - Shocks Exit Velocity [m/s]:
-  - 4603.893299749618
+  - 4618.009532317199
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/18500m/18500_altitude.yaml b/rockettests/18500m/18500_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 1515.5428024038706
+  - 6998.248139368094
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1549.4831828491194
+  - 1780.6919198598653
 - Shocks Exit Pressure [Pa]:
-  - 1515.5428024038706
+  - 6998.248139368094
 - Shocks Exit Velocity [m/s]:
-  - 4603.533204355715
+  - 4617.305810327982
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/18750m/18750_altitude.yaml b/rockettests/18750m/18750_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 1384.5804856484378
+  - 6728.88767860459
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1536.8047182523408
+  - 1774.3494096717657
 - Shocks Exit Pressure [Pa]:
-  - 1384.5804856484378
+  - 6728.88767860459
 - Shocks Exit Velocity [m/s]:
-  - 4603.204225817742
+  - 4616.629174385942
 - H2:
   - 0.23930995583841458
 - H:

diff --git a/rockettests/19000m/19000_altitude.yaml b/rockettests/19000m/19000_altitude.yaml
@@ -5,7 +5,7 @@
   Oxygen Mole Fraction:
   - 0.2095
   Pressure [Pa]:
-  - 1264.9349910789215
+  - 6469.894820757962
   Temperature [K]:
   - 216.67999999999998
 - Combustion Chamber Mechanism:
@@ -55,11 +55,11 @@
 - Shocks Mechanism:
   - NONE
 - Shocks Exit Temperature [K]:
-  - 1524.229993706639
+  - 1768.0294903850106
 - Shocks Exit Pressure [Pa]:
-  - 1264.9349910789213
+  - 6469.894820757963
 - Shocks Exit Velocity [m/s]:
-  - 4602.903675240647
+  - 4615.978581957292
 - H2:
   - 0.23930995583841458
 - H: