An aircraft with nose M1 P1 T1 properties of the upstream unifrom air M2 angle 0 = 15° as shown in figure, flies with Mach number M1 %3D = 2.5. The %3D are P1 = 60 kPa, and T = 265 K. Find: %3D

Q: If a calorically perfect gas flow is steady, isentropic and one dimensional, which of the following…

A: Solution: The state of a gas's thermodynamic variables can vary during an isentropic process. Gas is…

Q: Q3) A convergent-divergent nozzle has a cross-sectional area at the throat of 0.1 m² Air enters the…

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Q: The velocity of flow after a normal shock wave when (Tx= ,315 K, vx= 555 ms-1) 275.7 ms-1 O 396.1…

A:

Q: b) Air entering a converging-diverging nozzle at 1 MPa and 527 °C with negligible velocity…

A: To = 527 +273 = 800K Po = 1 MPa  Mass flow rate = 2.86 kg/s

Q: H2O gas enters a convergent-divergent nozzle, with pressure 5 MPa, and temperature 2000∘ C. Flow…

A: Given: To = 2000+273 = 2273 K Po = 5 MPa Correct option: 1100 m/s

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Q: Nitrogen gas at a stagnation temperature of 300 K and a static pressure of 2 bar flows adiabatically…

A: Given: Stagnation temperature of nitrogen gas St=300 K Static pressure of nitrogen sp=2 bar The…

Q: The velocity of flow after a normal shock wave when (Tx= 315 K, vx= 555 ms-1)

A:

Q: 2.106 The pressure, temperature, and velocity of a high speed gas flow are 100kPa, 100 °C, and 930…

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Q: flow by 15", as shown in the fīgure flow are 40 kPa and 263 K. respec

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Q: Q.5. With careful design, one can orient the bend on the lower wall so that the reflected wave is…

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Q: 3- Mach number at a certain section in a diverging part of a c-d nozzle is 0.7. At farther section…

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Q: A flow undergoes a normal shock just past a section where the area is 53 cm²: p= 12 kPa, p = 0.182…

A:

Q: Q2: Helium in a isentropically process. What are the lowest temperature and pressure that can be…

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Q: 1- Calculate the pressure, temperature and velocity prior to the shock wave. 2- Determine if the…

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Q: This year's qualification round featured a spaceship escaping The crew survived and wants to study…

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Q: The velocity of flow after a normal shock wave when (Tx= 315 K, vx= 555 ,ms-1) 275.7 ms-1 O 282.6…

A: Given: Temperature (T) = 315 K Velocity (Vx) = 555 m/s To find: Velocity after shock

Q: During the Rayleigh process if the flow is subsonic, due to cooling the velocity remains constant…

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Q: 56. A supersonic aircraft flies with a velocity greater by 39 m-s1 at 7600 m elevation, (T = - 51 C°…

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Q: Air flows in the channel in the figure below. The pressure at station 1 is 59 psia. Determine the…

A: Given data:

Q: Activity No. 1 Title: Pressure, Density. Temperature, and Mach Number Changes Across a Normal Shock…

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Q: 1) What is the value of static temperature, stagnation temperature and stagnation pressure in the…

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Q: Q2/ Air flows isentropically in a converging-diverging nozzle with initial Ma = 0.2, pressure = 1…

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Q: 2- Conditions before a shock are T1 = 40°C, pl = 1.2 bar, and M1 = 3.0. An oblique shock is observed…

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Q: a) Derive an expression for a relation between pressure and area changes in one- dimensional, steady…

A: a) Since, h0=h+V22differentiating we get0=dh+VdVdh=-VdV.....equation 1 From property relation,…

Q: 7. As air flows through a shock wave: a. static pressure increases, density decreases, temperature…

A: As per our guidelines we are suppose to answer first three questions. 7. Across a shock wave, the…

Q: H2O gas enters a convergent-divergent nozzle, with pressure 5 MPa, and temperature 2000∘ C. Flow…

A: Givenstagnation temperature = 2000 deg C stagnation pressure = 5 MPa exit temperature = 909 K

Q: he entropy change across a normal shock wave (Tox= 505 K, vx= 490 ms-1)

A: Given data: Tox = 505 K Vx = 490 m/s For air, specific heat, cp = 1.005 kJ/kg.K = 1005 /kg.K Gas…

Q: Q2) Air (Y=1.4 and R=287 J/kg.k) flow through a converging - diverging nozzle designed to operate…

A: Air   Y = 1.4  R = 287 J/kg-K  d1 = 43 mm  d* = 25 mm  P1 = 86 kPA  T1 = 298 K  P2 = 12kPa

Q: 8. Air is flowing through a wide channel at a Mach number of 2 at a pressure of 140 kPa. The upper…

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Q: The stagnation pressure across ,a normal shock wave is always poy ≥ pox O poy = pox O poy pox O

A: Option: is correct  poy < pox Because across the normal shock wave the stagnation pressure…

Q: True or False: 1. As temperature rises, mach number is greater 2. An airplane flying with mach…

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Q: Stagnation density for Of 200 0 (b A flow of air passing through a duct has static pressure values…

A: Given data:Static pressure at first position: P1 = 3.5 barStatic temperature at first position: T1 =…

Q: 70. A supersonic airplane flies at two altitudes find the temperature of air at second level, (v2…

A: Now according to given data we haveMa=VCV=Velocity of planeC=Velocity of sound in air at particular…

Q: H2O gas enters a convergent-divergent nozzle, with pressure 5 MPa, and temperature 2000∘ C. Flow…

A: Given: Let us consider the given, Stagnant Temperature, T0=2000°C+273=2273 k Exit temperature,…