准一维流动.Consider a convergent-divergent duct with exit and throat areas of 0.5 m2 and 0.25m2,respectively.The inlet reservoir pressure is 1 atm and the exit static pressure is 0.6 atm.For this pressure ratio,the flow will be supersonic in a p

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准一维流动.Consideraconvergent-divergentductwithexitandthroatareasof0.5m2and0.25m2,respectively.Theinletr

准一维流动.Consider a convergent-divergent duct with exit and throat areas of 0.5 m2 and 0.25m2,respectively.The inlet reservoir pressure is 1 atm and the exit static pressure is 0.6 atm.For this pressure ratio,the flow will be supersonic in a p
准一维流动.
Consider a convergent-divergent duct with exit and throat areas of 0.5 m2 and 0.25m2,respectively.The inlet reservoir pressure is 1 atm and the exit static pressure is 0.6 atm.For this pressure ratio,the flow will be supersonic in a portion of the nozzle,terminating with a normal shock inside the nozzle.Calculate the local area ratio (A/A*) at which the shock is located inside the nozzle.

准一维流动.Consider a convergent-divergent duct with exit and throat areas of 0.5 m2 and 0.25m2,respectively.The inlet reservoir pressure is 1 atm and the exit static pressure is 0.6 atm.For this pressure ratio,the flow will be supersonic in a p
Modern compressible flow by John D Anderson
Eq. (5.28)
Eq. (5.24)
= (0.6/1) × (0.5/0.25) = 1.2
Me2 = -1/(1.4 - 1) + √(1/(1.4-1)^2 +2/(1.4-1)×〖(2/(1.4+1))〗^((1.4+1)/(1.4-1))×〖(1/1.2)〗^2 ) = 0.223
From Table Isentropic flow properties
Mepoe/pe
0.2201.0343
Eq. (5.29)
po2/po1 = 1.0343 × (0.6/1) = 0.621
From Table Normal shock properties
Mpo2/po1
1.22000.6281
From Table Isentropic flow properties
MA/A*
1.22001.0366
The local area ratio at which the shock is located inside the nozzle is 1.0366

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