turbojet

turbojet - Parameter Values in use Ideal cycle...

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Unformatted text preview: Parameter Values in use Ideal cycle "Real" cycle Description M_1_default 0.8000 0.8000 0.8000 Default flight gamma_default 1.4000 1.4000 1.4000 Default spec MW_default 0.0290 0.0290 0.0290 Default gas m T_1_default 250.0000 250.0000 250.0000 Default amb P_1_default 0.2500 0.2500 0.2500 Default amb n_diffuser_default 1.0000 1.0000 0.9500 Default inlet gamma_d 1.4000 1.4000 1.4000 Specific hea Pi_c_default 30.0000 30.0000 20.0000 Default comp n_comp 1.0000 1.0000 0.9000 Default comp gamma_c 1.4000 1.4000 1.3800 Specific hea Pi_fan_default 2.0000 2.0000 2.0000 Default fan p n_fan_default 1.0000 1.0000 0.9500 Default fan e gamma_f 1.4000 1.4000 1.4000 Specific hea alpha_fan_default 0.0000 0.0000 0.0000 Default bypa Afterburner_default FALSE FALSE FALSE Default after Tau_lamda_default 5.0000 5.0000 5.0000 Default value Pi_burner_default 1.0000 1.0000 0.9500 Default burn n_burner 1.0000 1.0000 0.9900 Default burn gamma_b 1.4000 1.4000 1.3000 Specific hea nturb_default 1.0000 1.0000 0.9200 Default turbi gamma_t 1.4000 1.4000 1.2900 Specific hea Tau_lam_ab 7.0000 7.0000 7.0000 Default value Pi_ab_default 1.0000 1.0000 0.9500 Default after n_ab 1.0000 1.0000 0.9900 Default after gamma_ab 1.4000 1.4000 1.3000 Specific hea P_9_default 0.2500 0.2500 0.2500 Exit pressure n_nozzle_default 1.0000 1.0000 0.9500 Default nozz gamma_n 1.4000 1.4000 1.3200 Specific hea drag_coeff 0.0000 0.0000 0.0100 Inlet drag co t Mach number cific heat ratio (same throughout cycle unless overridden) molecular weight (kg/mole) (assumed constant throughout cycle) ient temperature (K) ient pressure (atm) t diffuser efficiency at ratio for diffuser (default value = gamma_default) pressor pressure ratio pressor efficiency at ratio for compressor (default value = gamma_default) pressure ratio efficiency at ratio for fan (default value = gamma_default) ass ratio (mass flow through fan / mass flow through core stream) rburner on/off (false = no afterburner) e of (turbine inlet temperature limit /ambient temperature) ner pressure ratio ner efficiency (actual fuel input / ideal fuel input if no heat losses) at ratio for burner (default value = gamma_default) ine efficiency at ratio for turbine (default value = gamma_default) e of (afterburner temperature limit /ambient temperature) rburner pressure ratio rburner efficiency (actual fuel input / ideal fuel input if no heat losses) at ratio for afterburner (default value = gamma_default) re (atm) (default = ambient pressure) zle efficiency at ratio for nozzle (default value = gamma_default) oefficient (drag/area = drag_coeff*(1/2)*rho*u1^2) M_1 0.0001 0.1001 0.2001 0.3001 0.4001 0.5001 0.6001 MW 0.0290 0.0290 0.0290 0.0290 0.0290 0.0290 0.0290 T_1 250.0000 250.0000 250.0000 250.0000 250.0000 250.0000 250.0000 P_1 0.2500 0.2500 0.2500 0.2500 0.2500 0.2500 0.2500 Rgas...
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This note was uploaded on 07/22/2008 for the course AME 436 taught by Professor Ronney during the Spring '08 term at USC.

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turbojet - Parameter Values in use Ideal cycle...

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