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4.) Air flows adiabatically through a duct. At point (1) the velocity is 200 m/s with a temperature of 310 K and pressure of
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soin The vero velocity of the pressure wave ve; vorc=VORT V11.4) (287) 310 Von C = 352.927 M m/s The mach number Ma= 는 V 200YK-1 TO1 To (fo) =( fo, = (2.023) * ( 1-4-1 329.911 310 to, = 2.3636 4 Ano. kg / m3 ₂ Vmax ni Vmax ( 2 Cp To th (2x1005 x 329At state-2 ation temp since the frow in adiabatic, stagnation : Тоа 2. Та : То, vz² То, 2 е 3a9:41 - 2 2 2Х 165 Та 243 •642 к

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