AirCycles4Propulsion

AirCycles4Propulsion - Gas properties Intake conditions...

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Unformatted text preview: Gas properties Intake conditions M (kg/mole) R (j/kgK) Qr Tintake (K) 0.03 286.7 1.4 4.50E+07 300 Diffuser Compressor Combustor Turbine Afterburner Property 1 Tau_lamda Property 1 value 0.00 10.97 5 7 Property 2 Afterburner on Property 2 value FALSE 1 1 1 1 1 gamma 1.4 1.4 1.4 1.4 1.4 Wall temp 300 300 900 900 900 Calculated results (don't modify these cells!) f FAR ue (m/s) Ae (m^2) 3.27E+00 0.0185 0.0188 9.985E+02 6.217E-03 2.419E+03 gamma (default) COMPONENT PROPERTIES Mach no. after diffuser Compressor press. ratio Tau_lamda,A B Component efficiency Main flow mdot_a (kg/s) Main thrust (N) 0.0 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 1.8 2.0 0.0 5.0 10.0 15.0 20.0 P-v diagram Diffuser Compressor Combustor Turbine (comp) Turbine (fan) Afterburner Nozzle Close the cycle 1.000 1.524 16.722 16.722 6.957 6.957 6.957 1.000 Specific volume (m^3/kg) Pressure (atm)-4 200 400 600 800 1000 1200 1400 1600 Diffus Turbin 300.0 1167.5 Temperature (K) Diffuser gamma= 1.40 Cp = 1003.41 P (atm) Pt (atm) T (adia) (K) Tt Tt (after xfer) v (m^3/kg) 1.000 1.524 300.0 338.4 338.4 0.8488 1.032 1.524 302.7 338.4 338.4 0.8301 1.063 1.524 305.3 338.4 338.4 0.8123 1.095 1.524 307.9 338.4 338.4 0.7955 1.126 1.524 310.4 338.4 338.4 0.7797 1.157 1.524 312.8 338.4 338.4 0.7648 1.188 1.524 315.1 338.4 338.4 0.7507 1.217 1.524 317.3 338.4 338.4 0.7376 1.246 1.524 319.5 338.4 338.4 0.7252 1.275 1.524 321.5 338.4 338.4 0.7137 1.302 1.524 323.5 338.4 338.4 0.7030 1.328 1.524 325.3 338.4 338.4 0.6931 1.353 1.524 327.1 338.4 338.4 0.6839 1.377 1.524 328.7 338.4 338.4 0.6755 1.399 1.524 330.2 338.4 338.4 0.6678 1.420 1.524 331.6 338.4 338.4 0.6608 1.439 1.524 332.9 338.4 338.4 0.6545 1.456 1.524 334.0 338.4 338.4 0.6489 1.472 1.524 335.0 338.4 338.4 0.6440 1.486 1.524 335.9 338.4 338.4 0.6398 1.497 1.524 336.7 338.4 338.4 0.6362 1.507 1.524 337.3 338.4 338.4 0.6333 1.515 1.524 337.8 338.4 338.4 0.6310 1.520 1.524 338.1 338.4 338.4 0.6294 1.523 1.524 338.3 338.4 338.4 0.6284 1.524 1.524 338.4 338.4 338.4 0.6281 Compressor gamma= 1.40 Cp = 1003.41 P (atm) Pt (atm) T (adia) (K) Tt Tt (after xfer) v (m^3/kg) 1.524 1.524 338.4 338.4 338.4 0.6281 2.132 2.132 372.5 372.5 372.5 0.4942 2.740 2.740 400.1 400.1 400.1 0.4132 3.348 3.348 423.7 423.7 423.7 0.3581 3.956 3.956 444.4 444.4 444.4 0.3178 4.564 4.564 462.9 462.9 462.9 0.2870 5.172 5.172 479.8 479.8 479.8 0.2625 5.780 5.780 495.2 495.2 495.2 0.2424 6.388 6.388 509.6 509.6 509.6 0.2257 6.996 6.996 523.0 523.0 523.0 0.2115 7.603 7.603 535.6 535.6 535.6 0.1993 8.211 8.211 547.5 547.5 547.5 0.1887 8.819 8.819 558.8 558.8 558.8 0.1793 9.427 9.427 569.5 569.5 569.5 0.1709 10.035 10.035 579.8 579.8 579.8 0.1635 10.643 10.643 589.6 589.6 589.6 0.1567 11.251 11.251 599.0 599.0 599.0 0.1507 11.859 11.859 608.1 608.1 608.1 0.1451 12.467 12.467 616.9 616.9 616.9 0.1400 13.075 13.075 625.3 625.3 625.3 0.1353 13.682 13.682 633.5 633.5 633.5 0.1310 14.290 14.290 641.4 641.4 641.4 0.1270 14.89814....
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AirCycles4Propulsion - Gas properties Intake conditions...

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