Problem 13.4 - p 01 = p 02, A * 2 = A * 1 ) p 02 = 624 kPa...

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Problem 13.4 [Difficulty: 2] Given: Data on flow in a passage Find: Pressure and Mach number at downstream location Solution: The given or available data is: R = 296.8 J/kg-K k = 1.4 p 1 = 450 kPa M 1 = 0.7 A 1 = 0.15 m 2 A 2 = 0.45 m 2 Equations and Computations: From M 1 and p 1 , and Eq. 13.7a (using built-in function Isenp ( M , k )) p 01 = 624 kPa From M 1 , and Eq. 13.7d (using built-in function IsenA ( M , k )) A * 1 = 0.1371 m 2 For isentropic flow (
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Unformatted text preview: p 01 = p 02, A * 2 = A * 1 ) p 02 = 624 kPa A * 2 = 0.1371 m 2 A 2 /A * 2 = 3.2831 From A 2 / A * 2 , and Eq. 13.7d (using built-in function IsenMsubfromA ( M , k )) Since there is no throat, the flow stays subsonic M 2 = 0.1797 From M 2 and p 02 , and Eq. 13.7a (using built-in function Isenp ( M , k )) p 2 = 610 kPa...
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