diff --git a/F_thrust_RASAERO.txt b/F_thrust_RASAERO.txt
new file mode 100644
index 0000000..7ef2ea5
--- /dev/null
+++ b/F_thrust_RASAERO.txt
@@ -0,0 +1,32 @@
+; Name diameter(mm) Length(mm) delay propellant_weight(kg) mass(kg)
+O6900-I 143 2438 P 3.85 15.79 SSI
+0.010 1320.418
+0.200 1561.631
+0.400 1546.229
+0.590 1531.306
+0.790 1516.129
+0.980 1500.406
+1.180 1482.341
+1.370 1466.933
+1.570 1451.104
+1.760 1434.491
+1.960 1417.684
+2.150 1401.527
+2.350 1384.385
+2.540 1368.230
+2.740 1352.983
+2.930 1337.996
+3.130 1322.032
+3.320 1307.148
+3.520 1290.261
+3.710 1275.134
+3.910 1259.703
+4.100 1245.385
+4.300 1230.102
+4.490 1215.732
+4.690 1200.258
+4.880 490.540
+5.080 428.407
+5.270 376.835
+5.470 329.905
+5.655 0.000
diff --git a/Supporting Functions/HybridModel.m b/Supporting Functions/HybridModel.m
new file mode 100644
index 0000000..68a09fc
--- /dev/null
+++ b/Supporting Functions/HybridModel.m	
@@ -0,0 +1,70 @@
+function x_dot = HybridModel(time,x,inputs,mode)
+% Model engine physics for a hybrid motor, provide state vector derivative
+
+%% Initialization of State Properties
+state = HybridStateVector.FromColumnVector(x, inputs, mode);
+
+state_dot = HybridStateVector();
+
+%% Calculate Injector Mass Flow Rate
+[m_dot_lox, m_dot_gox, m_dot_oxtank_press, T_dot_drain, p_crit, m_dot_ox_crit] = ...
+    N2OTankMDot(inputs, state, time);
+[m_dot_vap, T_dot_vap] = N2OTankEquilibrium(inputs, state);
+
+state_dot.m_lox = -m_dot_lox - m_dot_vap;
+state_dot.m_gox = -m_dot_gox + m_dot_vap;
+state_dot.m_oxtank_press = -m_dot_oxtank_press;
+state_dot.T_oxtank = T_dot_drain + T_dot_vap; 
+
+m_dot_ox = m_dot_lox + m_dot_gox;
+
+%% Combustion Dynamics
+if mode.combustion_on % for hot fire only 
+    [m_dot_f, r_dot] = HybridMdotFuel(inputs, state, m_dot_ox);
+    
+    [F_thrust, OF, M_e, p_exit, p_shock, m_cc_dot, M_cc_dot, ...
+    gamma_cc_dot, T_cc_dot] = CombustionChamber(inputs, state, m_dot_ox, m_dot_f);
+else % no combustion (cold flow)
+    m_dot_f = 0;
+    r_dot = 0;
+    
+    F_thrust = 0;
+    OF = 0;
+    M_e = 0;
+    p_exit = inputs.p_amb;
+    p_shock = 0;
+    m_cc_dot = 0;
+    M_cc_dot = 0;
+    gamma_cc_dot = 0;
+    T_cc_dot = 0;
+end
+state_dot.m_fuel = -m_dot_f;
+state_dot.m_cc = m_cc_dot;
+state_dot.M_cc = M_cc_dot;
+state_dot.gamma_cc = gamma_cc_dot;
+state_dot.T_cc = T_cc_dot;
+
+%% Pressurant Flow
+if inputs.ox_pressurant.active
+    [T_dot_press, m_dot_press] = PressurantFlow(state.p_oxpresstank, ...
+        state.T_oxpresstank, state.p_oxtank, state.T_oxtank, ...
+        state.oxtank_m_cv, inputs.ox_pressurant);
+else
+    T_dot_press = 0;
+    m_dot_press = 0;
+end
+state_dot.T_oxtank = state_dot.T_oxtank + T_dot_press;
+state_dot.m_oxtank_press = m_dot_press;
+state_dot.m_oxpresstank = -m_dot_press;
+
+%% Generate column vector
+x_dot = state_dot.ColumnVector;
+HybridRecord(time, state, state_dot, F_thrust, p_crit, ...
+    m_dot_ox_crit, M_e, p_exit, p_shock);
+
+% fprintf('time: %.3f \n', time)
+% fprintf('%.3g\t', x_dot)
+% fprintf('\n')
+% fprintf('%% (Ptank - Pvap)/Pvap: %.1f\n', 100*(state.p_gox - state.N2O_properties.Pvap)/state.N2O_properties.Pvap)
+
+end
\ No newline at end of file
diff --git a/Supporting Functions/Integration.m b/Supporting Functions/Integration.m
index 698ccb1..0a4e8b4 100644
--- a/Supporting Functions/Integration.m	
+++ b/Supporting Functions/Integration.m	
@@ -117,76 +117,7 @@
 end
 end
 
-function x_dot = HybridModel(time,x,inputs,mode)
-% Model engine physics for a hybrid motor, provide state vector derivative
 
-%% Initialization of State Properties
-state = HybridStateVector.FromColumnVector(x, inputs, mode);
-
-state_dot = HybridStateVector();
-
-%% Calculate Injector Mass Flow Rate
-[m_dot_lox, m_dot_gox, m_dot_oxtank_press, T_dot_drain, p_crit, m_dot_ox_crit] = ...
-    N2OTankMDot(inputs, state, time);
-[m_dot_vap, T_dot_vap] = N2OTankEquilibrium(inputs, state);
-
-state_dot.m_lox = -m_dot_lox - m_dot_vap;
-state_dot.m_gox = -m_dot_gox + m_dot_vap;
-state_dot.m_oxtank_press = -m_dot_oxtank_press;
-state_dot.T_oxtank = T_dot_drain + T_dot_vap; 
-
-m_dot_ox = m_dot_lox + m_dot_gox;
-
-%% Combustion Dynamics
-if mode.combustion_on % for hot fire only 
-    [m_dot_f, r_dot] = HybridMdotFuel(inputs, state, m_dot_ox);
-    
-    [F_thrust, OF, M_e, p_exit, p_shock, m_cc_dot, M_cc_dot, ...
-    gamma_cc_dot, T_cc_dot] = CombustionChamber(inputs, state, m_dot_ox, m_dot_f);
-else % no combustion (cold flow)
-    m_dot_f = 0;
-    r_dot = 0;
-    
-    F_thrust = 0;
-    OF = 0;
-    M_e = 0;
-    p_exit = inputs.p_amb;
-    p_shock = 0;
-    m_cc_dot = 0;
-    M_cc_dot = 0;
-    gamma_cc_dot = 0;
-    T_cc_dot = 0;
-end
-state_dot.m_fuel = -m_dot_f;
-state_dot.m_cc = m_cc_dot;
-state_dot.M_cc = M_cc_dot;
-state_dot.gamma_cc = gamma_cc_dot;
-state_dot.T_cc = T_cc_dot;
-
-%% Pressurant Flow
-if inputs.ox_pressurant.active
-    [T_dot_press, m_dot_press] = PressurantFlow(state.p_oxpresstank, ...
-        state.T_oxpresstank, state.p_oxtank, state.T_oxtank, ...
-        state.oxtank_m_cv, inputs.ox_pressurant);
-else
-    T_dot_press = 0;
-    m_dot_press = 0;
-end
-state_dot.T_oxtank = state_dot.T_oxtank + T_dot_press;
-state_dot.m_oxtank_press = m_dot_press;
-state_dot.m_oxpresstank = -m_dot_press;
-
-%% Generate column vector
-x_dot = state_dot.ColumnVector;
-HybridRecord(time, state, state_dot, F_thrust, p_crit, ...
-    m_dot_ox_crit, M_e, p_exit, p_shock);
-
-% fprintf('time: %.3f \n', time)
-% fprintf('%.3g\t', x_dot)
-% fprintf('\n')
-% fprintf('%% (Ptank - Pvap)/Pvap: %.1f\n', 100*(state.p_gox - state.N2O_properties.Pvap)/state.N2O_properties.Pvap)
-
-end
 
 function x_dot = LiquidModel(time,x,inputs,mode)
 % Model engine physics for a liquid motor, provide state vector derivative