AirCycles4Hypersonics

AirCycles4Hypersonics - 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 1.20E+08 227 Diffuser Combustor Combustor Nozzle Property 1 Tau_lamda Const. T? Pexh (atm) Property 1 value 2.63 35.9 TRUE 0.01 Property 2 Const. P? Const. A? <--- Default com Property 2 value FALSE FALSE 1 1 gamma 1.4 1.4 1.4 Wall temp 227 4188.15 4188.15 Calculated results (don't modify these cells!) f FAR ue (m/s) Ae (m^2) 5.08E-01 0.0283 0.0291 3.726E+03 4.395E-02 4.141E+02 gamma (default) COMPONENT PROPERTIES Mach no. after diffuser Component efficiency Main flow mdot_a (kg/s) Main thrust (N) 1000 2000 3000 4000 5000 6000 7000 8000 9000 T-s diagram Diffuser Combustor Nozzle Close the cycle Rayleigh from 1 Rayleigh from 2 227.0 2,000.101 2000.1 1231.5 Temperature (K) 1 1 1 1 1. Diffu 0.00 Com 3.92 Area (m^2) Diffuser gamma= 1.40 Cp = 1003.41 P (atm) Pt (atm) T (adia) (K) Tt Tt (after xfer) v (m^3/kg) 1 0.011 458.344 227.0 4767.0 4767.0 59.4699 2 0.013 458.344 240.3 4767.0 4767.0 51.5827 3 0.016 458.344 254.8 4767.0 4767.0 44.5655 4 0.020 458.344 270.6 4767.0 4767.0 38.3435 5 0.025 458.344 287.8 4767.0 4767.0 32.8462 6 0.031 458.344 306.8 4767.0 4767.0 28.0075 7 0.039 458.344 327.6 4767.0 4767.0 23.7655 8 0.049 458.344 350.6 4767.0 4767.0 20.0623 9 0.063 458.344 376.0 4767.0 4767.0 16.8440 10 0.081 458.344 404.2 4767.0 4767.0 14.0606 11 0.106 458.344 435.5 4767.0 4767.0 11.6655 12 0.138 458.344 470.5 4767.0 4767.0 9.6157 13 0.183 458.344 509.7 4767.0 4767.0 7.8717 14 0.245 458.344 553.8 4767.0 4767.0 6.3972 15 0.331 458.344 603.6 4767.0 4767.0 5.1586 16 0.453 458.344 660.0 4767.0 4767.0 4.1259 17 0.626 458.344 724.2 4767.0 4767.0 3.2713 18 0.878 458.344 797.6 4767.0 4767.0 2.5700 19 1.248 458.344 881.8 4767.0 4767.0 1.9996 20 1.798 458.344 978.9 4767.0 4767.0 1.5401 21 2.630 458.344 1091.2 4767.0 4767.0 1.1738 22 3.906 458.344 1221.7 4767.0 4767.0 0.8850 23 5.888 458.344 1373.7 4767.0 4767.0 0.6601 24 9.008 458.344 1551.2 4767.0 4767.0 0.4872 25 13.973 458.344 1758.5 4767.0 4767.0 0.3561 26 21.929 458.344 2000.1 4767.0 4767.0 0.2581 Combustor gamma= 1.40 Cp = 1003.41 P (atm) Pt (atm) T (adia) (K) Tt Tt (after xfer) v (m^3/kg) 26 21.929 458.344 2,000.101 4,767.000 4,767.000 0.258 27 17.306 398.944 2,000.101 4,902.292 4,902.292 0.327 28 13.658 346.317 2,000.101 5,037.584 5,037.584 0.414 29 10.778 299.874 2,000.101 5,172.876 5,172.876 0.525 30 8.506 259.038 2,000.101 5,308.168 5,308.168 0.665 31 6.713 223.255 2,000.101 5,443.460 5,443.460 0.843 32 5.298 191.999 2,000.101 5,578.752 5,578.752 1.068 33 4.181 164.780 2,000.101 5,714.044 5,714.044 1.354 34 3.300 141.142 2,000.101 5,849.336 5,849.336 1.715 35 2.604 120.669 2,000.101 5,984.628 5,984.628 2.173 36 2.055 102.981 2,000.101 6,119.920 6,119.920 2.754 37 1.622 87.735 2,000.101 6,255.212 6,255.212 3.489 38 1.280 74.624 2,000.101 6,390.504 6,390.504 4.421 39 1.010 63.373 2,000.101 6,525.796 6,525.796 5.602 40 0.797 53.738 2,000.101 6,661.0886,661....
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This note was uploaded on 07/22/2008 for the course AME 514 taught by Professor Ronney during the Fall '06 term at USC.

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AirCycles4Hypersonics - Gas properties Intake conditions...

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