Question

Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic 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) = 321
Inlet pressure: P1 (kPa) = 588
Inlet Velocity: V1 (m/s) = 97
Area at nozzle inlet: A1 (cm^2) = 6.36
Throat area: A (cm^2) = 3.22
Area at diffuser exit: A (cm^2) = 4.35

a) Determine the Mach number at the inlet.
        Your Answer = Correct! Exact Answer= 0.2701 +/- 9.4E-04
b) Determine the stagnation temperature (K) at the inlet.
        Your Answer = Correct! Exact Answer= 325.68 +/- 1.4E+00
c) Determine the stagnation pressure (kPa) at the inlet.
        Your Answer = Correct! Exact Answer= 618.58 +/- 2.4E+00
d) Determine the theoretical throat area (cm^2) for sonic flow (A*).
        Your Answer = Correct! Exact Answer= 2.842 +/- 1.2E-02
e) Determine the Mach number at the throat.
        Your Answer = Incorrect.
f) Determine the temperature (K) at the throat.
        Your Answer =
g) Determine the velocity (m/s) at the throat.
        Your Answer =
h) Determine the pressure (kPa) at the throat.
        Your Answer =
i) Determine the mass flow rate (kg/s) through the nozzle
        Your Answer =
j) Determine the Mach number at the exit.
        Your Answer =
k) Determine the temperature (K) at the exit.
        Your Answer =
l) Determine the velocity (m/s) at the exit.
        Your Answer =

Answer 1

Solution we have V ma 0.2100 77.4.X28+X 321 :. madh number at inlet = 0.2700 (b) То с т у 2. 2Cp (972 ax1005 321 + = 325.68 (C) Do P [!+ Tiga Dima? j***?. 1042] 1.4/1.4-1 Po . It does 588 0.2704 Po = 678.58 we have 113.300 3.22 2.842 (f) we have To 1+ 1) ma? 32 5.6831+ 10:42.) 10.270132 T = 311 529 K. (g) we have V - и ch Vam not a ROTO 1.4 x 287x311.579 V.0..631 V=223:24 mis. velocity of the throat 2223.24 m/s.

5. we have K/R-11 Ро Р [1+ Cread mar] =[ + 012.(0:270172] 14% 1.91 618.58 P press wie Pe 170.0.67 ek pa: at rie the rout : :170:67 k pai ci mars frow rate inrough the nozzle in k ..Pi Alma RTI lon 588X10%(8078 701210) 287 X 321 588 X103 x 3.22 x 10-4 %0.2701 1.4 28.7.X321 12.0• 77.71 kg16 US А 4.35 5.59. Aa 0.737) 0.42222. mach number at ex it-

(K) we hare To 1 + (k-1) ma? TEK 325:68 1+ (0-2) (0,42227% ti T= 31.7.997 R. Temperature et the exit = 317.997k (l ma soma с кет 02 701 Vroux 287 x 317.99 96.5.4 mls. nie exit 9.6. su mis. i velours at

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