Question

Homework Problem IW8 3 Attemps Used 20 Due DateThu, Jul 30, 2020, 23:59:59 Current Time Thu, Jul 30, 2020, 00:02:48 Air flows through a converging-diverging nozzle/differ. Assuming isentropic flow, air as an ideal gas, and constant specific heat determine the state at several locations in the system Note: The specific heat ratio and gas constant for air are given ask-1A od R-0.287 kg K respectively --Given Vues Inlet Temperature: TI (K) 358 Inlet pressure: PI (kPa) - 626 Inlet Velocity: V1 (m/s) - 83 Area at inlet (cm2) - 7.8 Mach number at the exit - 2.38 a) Determine the mass flow rate (kg/s) through the nozzle Your Anwer b) Determine the Mach number at the inlet Your Answer c) Determine the stagnation temperature (K) at the inlet Your Auwwer d) Determine the stagnation pressure (kPa) at the inlet, Your Answer e) Determine the temperature (K) at the throat, Your Answer 1) Determine the pressure (kPa) at the throat. Your Answer hth

Answer 1

m = exa XV BT,VI A m 2 2.38 a. m = P. RT .X AXV = 626x103 287 x 358 X 7.8x16" 83 m = 0.394 kg/see b. Mach Numbe & V 83 SERT, = 0.218 p-4x287 X358 c . T. To en la mano a 7+ 358/14 cm x 0-180 To= 361-4 k K d. 6.4 Po Р ( 14 K 1 m 9 Po = 626 / 1+ or x 0.218 sora7% Po= 647.07 kPa throat mach No. 1 fi At K 16-1 0.4 K-1 = 1.892 = 1 = 0.5287 Pe PE f = 341.79 kla e. To Tt To E1.29 TL = 0.833.7 те =1+ 2 , I = 301.16 K