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) 370 Inlet pressure: P1 (kPa) = 576 Inlet Velocity: V1 (m/s) - 106 Area at nozzle inlet: A1 (cm^2) = 8.32 Throat area: A (cm^2) = 4.1 Area at diffuser exit: A (cm^2)= 7.31 a) Determine the Mach number at the inlet. Your Answer = 1980 Incorrect. b) Determine the stagnation temperature (K) at the inlet. Your Answers Correct! Exact Answer=375.59 +/- 1.4E+00 c) Determine the stagnation pressure (kPa) at the inlet. Your Answer = 0.31 Correct! Exact Answer=607.05 +/- 2.4E+00 d) Determine the theoretical throat area (cm^2) for sonic flow (A*). Your Answer = 0.5282 Incorrect. e) Determine the Mach number at the throat. Your Answer = f) Determine the temperature (K) at the throat. Your Answer = g) Determine the velocity (m/s) at the throat. Your Answer=d 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 = 8092 Incorrect. 1) Determine the velocity (m/s) at the exit. Your Answer Incorrect. 39936

Answer 1

for the Given problem, Adithus. diver Air flows through converging. giny Nozze 0 (3) Given P3113 Initial Temperature (11) -370k Αν Pi: 576kpa Inlist velocity ne- 106mis Nozolu - AI 8.32 lm kalu R=0288 FJ Mg-k Throat Area - 4.16mv Araat Liftuser Exiri A £ 7-31cm @ Mach number (M) c (: V&RT . (14) (6.287) x103 x 370 385.57 M. 106 0.2749 385-87 st ay nation temperature (lo) at inlet, TO 2 1+ (k-1) m to 370t 370 (1.4-1) (0.2749) v To = 37859 2 k stagnation reasure (Po) at intet 20 (*) (375.51 *k-1 P 370 CS (canned with CamScanner Po= 607.04 kpa

For sonic flow, MC) 은 1 C=SKRI V=C P 2 Do RTO Truxe87 x 3765 607.04 0.2871103 x 375.59 ea 0.005 63 1943 12 08333 10 1 2 375.59108333 T* = 312-97k AIVA Va* -TART 1-41287 x 312-97 = 354.619 m.is 8.32 x W x 106= A ( 354-619) x A2 2-48em V re A Nii AaVz 8.32 x 106 = 4 x 2 Vy 215, 1024 mloce Mach Number 215-1024 ok 0.60 354-619 at throat' CS Scanned with CamScanner

(ع) velocity AINE Alle rX V v 6 po PAVI velocity at Exit , ANI= A3U3 at throat AV v -> 8.32X 1062 Vai 215 1024on IS Tem perature at throut, Ta 0.833) To The 312-97k Memure P2 0.5283 Pro 320-69 k pa Maan How rate (m): 0:88563 x 8.32 x 104 x 106 4.96 41034 kg/ (1) Exit, ANIE A 3V3 (8-325 x 106 - (7-31) «Vz Vz= 120.64 misec T/ 0-8333 tz. 8335 x 57555 70 to 6 V3 = norunts Scanned with es CamScanner Mach Number at 3 کام . --