# Chapter 09 - Selected Answers - 7 9.67 49.68 single stage...

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Answers to Selected Problems - 6e Chapter 9 9.5 (a) 0.5293, (b) 0.2989, (c) 56.5, (d) 8.54 9.9 r = 8, T 3 = 2000°R, 53.9%, 39.95 lbf/in.² 9.12 121.11, 58.5, 188.8 9.14 0.217, 36.8 9.21 22.01, 2.081, 65.7, 883.0 9.26 15.58, 3004.6, 56.5, 101.4 9.29 r c = 1.5: 1301.5, 189.2, 297.5, 59.4 9.32 r = 15, T 3 = 1200 K: 246.3, 3.065, 60.34 9.38 r = 15: 457.6, 342.4, 57.2, 1.54 9.43 49.8, 6.457 x 10 6 , 1.693 x 10 9 9.44 T 3 = 1500 K: compressor; 372.6, turbine; 833.3, 55.3 9.52 10,706, compressor exit temperature; 1227, turbine exit temperature; 1346.9, 35.04 9.57 η reg = 0.78: 39.8, 14.1 9.59 (a) 5158, 46.2, (b) 3242, 31.2, (c) 3242, 37.6 9.61 26.2, 65.2, 5.56 x 10
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Unformatted text preview: 7 9.67 49.68, single stage: 60.11 9.74 (AV) 1 = 3.93, (AV) b = 1.31, 27.34, 0.401 9.79 1.145 x 10 8 , 57.61, 4.025 x 10 7 , 3004 9.82 2878 9.84 10, 296.4 9.93 287.9, 75.1 9.95 (b) 71.4 9.99 9.97: -5950 (opposite to flow), 9.81: -6507 (opposite to flow) 9.103-6.283 (opposite to flow) 9.105 1118, 1382, 1059 9.114 (a) 418.2, 4.238, (b) 446.6, 4.456, (c) 432.0, 4.344 9.115 26.46 9.118 2.61, 3.096, 3.245 9.123 mass flow rate: 0.497, supersonic nozzle: M 2 = 2.20, 0.769. 204.9, subsonic diffuser: M 2 = 0.3079, 7.70, 395.6 9.127 M x = 1.8: 1.81, 2.87, 461, 5.94 x 10-2...
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## This homework help was uploaded on 04/10/2008 for the course MAE 251 taught by Professor Lewalle during the Spring '08 term at Syracuse.

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