1: //// Conditional Input Values
2: private double a_0 = 0; // Ambient Speed of Sound [ft/s]
3: private double T_0 = 0; // Free Stream Air Temperature [R]
4: private double P_0 = 0; // Free Stream Air Pressure [lb/ft^2]
5: private double Rho_0 = 0; // Free Stream Air Density [slugs/ft^3]
6: private double Rho_SL = 0; // Free Stream Air Density at Sea Level [slugs/ft^3]
7:
8: //// Output Values
9: public double U_7 = 0; // Core exhaust Speed
10: public double U_9 = 0; // Fan exhaust Speed
11: public double F_s = 0; // Specific Thrust
12: public double TSFC = 0; // Thrust Specific Fuel Consumption
13: public double SLTFSC = 0; // Thrust Specific Fuel Consumption at Sea Level
14: public double eta_p = 0; // Propulsive Efficiency
15: public double eta_t = 0; // Thermal Efficiency
16: public double eta_o = 0; // Overall Efficiency
17: public double f = 0; // Fuel to Air Mass Flow Ratio
18:
19: //// Private Scientific Constants (READ ONLY)
20: private double g = 32.2; // Gravity [ft/s^2]
21: private double gc = 1.4; // Ratio of Specific Heats [cold air](c_p/c_v)
22: private double gt = 1.33; // Ratio of Specific Heats [hot air](c_p/c_v)
23: private double cpc = 0.24; // Cold Air Specific Heat [BTU/(lmb-R)]
24: private double cpt = 0.276; // Hot Air Specific Heat [BTU/(lmb-R)]
25: private double Rc = (1.4 - 1) / 1.4 * 0.24 * 778; // Gas Constant, Cold Air, (BTU=778) -> [(ft-lbf)/(lbm R)]
26: private double Rt = (1.33 - 1) / 1.33 * 0.276 * 778; // Gas Constant, Cold Air, (BTU=778) -> [(ft-lbf)/(lbm R)]
27:
28: //// Private Internal Engine Data (READ ONLY)
29: private double tau_r; // Ram Temperature Ratio
30: private double pi_r; // Ram Pressure Ratio
31: private double eta_r; // Ram Efficiency
32: private double T0_2; // Stagnation Temperature @2
33: private double P0_2; // Stagnation Pressure @2
34: private double pi_d; // Deceleration Pressure Ratio
35: private double T0_3; // Stagnation Temperature @3
36: private double P0_3; // Stagnation Pressure @3
37: private double tau_c; // Compressor Temperature Ratio
38: private double eta_c; // Compressor Efficiency
39: private double pi_b; // Ideal Combustion
40: private double P0_4; // Combustion Pressure @4
41: private double tau_b; // Combustion Temperature Ratio
42: private double tau_lambda; // Overall Temperature Ratio
43: private double tau_f; // Fan Temperature Ratio
44: private double M_9; // Fan Exit Mach Number
45: private double eta_f; // Fan Efficiency
46: private double tau_t; // Turbine Temperature Ratio
47: private double T0_5; // Turbine Stagnation Temperature
48: private double P0_5; // Turbine Stagnation Pressure
49: private double pi_t; // Turbine Pressure Ratio
50: private double tau_n; // Nozzle Temp Ratio
51: private double P_7; // Exit Pressure = Free Stream Pressure
52: private double P0_7P7; // Stagnation to Static Pressure Ratio @ 7
53: private double P0_7; // Nozzle Exit Stagnation Pressure
54: private double T0_7; // Nozzle Exit Stagnation Temperature
55: private double T7T0; // Overall Temperature Ratio
56: private double T7; // Exit Temperature
57: private double M_7; // Core Exhaust Mach Number
58: public double U_0; // Freestream Velocity