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Homework Problem HW8 2 Attemps Used 2/20 Due Date - Thu, Jul 30, 2020, 23:59:59 Current...

Question:

Homework Problem HW8 2 Attemps Used 2/20 Due Date - Thu, Jul 30, 2020, 23:59:59 Current Time Thu, Jul 30, 2020, 01:42:09 Air
a) Determine the Mach number at the inlet. Your Answer 1061 Incorrect b) Determine the stagnation temperature (K) at the inle
Homework Problem HW8 2 Attemps Used 2/20 Due Date - Thu, Jul 30, 2020, 23:59:59 Current Time Thu, Jul 30, 2020, 01:42:09 Air flows through a converging-diverging nozzle/diffuser. A normal shock stands in the diverging section of the nozzle. Assuming sentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables Note: The specific heat ratio and gas constant for air are given as k-1.4 and R-0.287 kJ/kg-K respectively. --Given Values Inlet Temperature: T1 (K) - 340 Inlet pressure: PI (kPa) - 550 D Inlet Velocity: VI (m/s) - 124 Throat Area: A (cm/2) - 8.4 Pressure upstream of (before) shock: Px (kPa) - 148.5 Mach number at exit: M -0.16 a) Determine the Mach number at the inlet Your Answer 1061 Incorrect b) Determine the stagnation temperature (K) at the inlet. Your Answer-34765 Correct! Exact Answer: 34765+.12E+00 c) Determine the stagnation pressure (kPa) at the inlet. Your Answer - 569 92 Incorrect d) Determine the temperature (K) at the throat Your Answer 26855 Incorrect. c) Determine the velocity (ms) at the throat Your Answer 125 82 Incorrect :) Determine the pressure (kPa) at the throat, Answer- Incorrect
a) Determine the Mach number at the inlet. Your Answer 1061 Incorrect b) Determine the stagnation temperature (K) at the inlet. Your Answer=347 65 Correct Exact Answer: 347,65 +/- 1.2E+00 e) Determine the stagnation pressure (kPa) at the inlet. Your Answer 559.92 Incorrect d) Determine the temperature (K) at the throat. Your Answer 288.55 Incorrect e) Determine the velocity (m/s) at the throat. Your Answer - 125.82 Incorrect f) Determine the pressure (kPa) at the throat, Your Answer 295.38 Incorrect 2) Determine the mass flow rate (kg/) through the nozzle Your Answer 0.5957 Incorrect h) Determine the Mach number (Mx) just upstream of (before the shock, Your Answer -8.623 Incomect. i) Determine the maximum velocity (m/6) in the nozzle. Your Answer 0.387 Incorrect ) Determine the Mach number (My) just downstream of (after the shock. Your Answer k) Determine the stagnation pressure (kPa) after the shock. Your Answer 1) Determine the pressure (kPa) at the exit. Your Answer m) Determine the temperature (K) at the exit Your Answer n) Detennine the area (cm2) at the exit. Your Answer .) Determine the velocity (ms) at the exit. Your Answer $

Answers

Pi (1+0:2 Mail] 3. Ti = 340k P, = 550kpa VI 3 124m/s 20 Athout = 8.4cm Menit 2016 I p befose shock = P x = 148.5 kpa Inlet Mamut -CALXV thout = T8R Ishoul 11.4x287X290 ✓ thood - 341.357) Psh xh = Monorrtth 2. Johan = eshsout RT those Cthroat = 3.36 kfrom normal sock table A, -0.001571 m2 A m, = GIAN 0 42 25.68X0.001571 X 124 m = 1.09 Kgl Pa = 148.5*pa Esentropic flow B 148TE T2 -1.62 T3 = 162X Tz -1.62x200.10 [T =324.876 (Temp after shock) Sony point 3-4 (asentropic How) (Paz =Poy) a 1 Tos = toyTo Ти [1+0.263)?] {1+02 (Over] Tu = 33282 liol - 331 IC ko Te -881K Pe=lexRTO 656.44 = lex0.287X331 € 56.4 kg) is 2364.68ms z

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