solve show solutions, modern incompressible flow 4.7 An incident shock wave with wave angle = 30° impinges on a straight wall.If the upstream flow properties are M₁ = 2.8, p₁ = 1 atm, and T₁ = 300 K,calculate the pressure, temperature, Mach number, and total pressuredownstream of the reflected wave.

Answered: 4.7 An incident shock wave with wave…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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Q.5 A supersonic wind tunnel, which is shown in the figure, is fed from a large tank. The air is discharged to the atmosphere. The Mach number in the test section is 2.65 and a normal shock wave stands at the exit of the wind tunnel. The pressure at section 3 immediately after the normal shock wave is 100 kPa. The flow is isentropic except through the normal shock wave. Find: 1. Po, P1, P2 and M3. 2. If a Pitot tube is placed in the exit jet, then calculate the pressure measured by the Pitot tube. Po Test section Normal shock wave Exit Jet Pitot tube
Q2: A/ Air is flowing in a convergent nozzle. The stagnation pressure is 350 KPa, the stagnation temperature is 400 K and Mach number is 0.7. If the cross sectional area at this location is 10 x 10-3 m2 , find 1) The static temperature and static pressure 2) The velocity at this location. 3) The area and static temperature and static pressure at the exit where Mach number =1 4) The mas flow rate of nozzle
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Q3. A supersonic flow of air has a pressure of 1 x 105 N/m2 and M a temperature of 350 K. After expanding through a 35° turm, the Mach number is 3.5. Determine: Angles 8,,02 and 03. 0= ? Final flow properties p2 and T2. Figure Q3
d*, 2. Consider a normal shock wave in air where the upstream flow properties are u1 = 690 m/s, T1 = 288 K, and p1=1 atm. Calculate the velocity, temperature, and pressure downstream of the shock.
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Air at P1 = 1 MPa, T1 = 600 °C and V1 = 150 m/s enters a converging nozzle. The exit area is A2 = 50 cm2 and the back pressure is P2 = 0.7 MPa. What is the mass flow rate (kg/s) through the nozzle? What the is Mach number at the nozzle exit? What would be the flow rate you calculate if you assumed isothermal flow?
Q2: Air (y = 1.4) enters a converging-diverging diffuser with a Mach number of 2.8, static pressure pi of 100 kPa, and a static temperature of 20°C. For the flow situation shown in Figure, find the exit velocity, exit static pressure, and exit stagnation pressure. Ans: Ve = 55.093 m/s; Pe = 2236.678 kPa; Poe = 2252.44 kPa i M₁ = 2.8 A₁ = 0.10 m² A₂ = 0.50 m² A₁ = 0.25 m²
1.AB
What is the minimum nozzle-diameter ratio De/D0 for which we can safely neglect compressibility effects if V0 = 10 m/s?
Q4//B/ Heat is removed from airflow in a constant-area duct, if flow enters at Mach 2.20, T1= 310 K, and p1= 120 kPa. Determine exit Mach number and the amount of heat removing from the duct if the static temperature at exit section is 255 K. justify your solution for M2

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4.7 An incident shock wave with wave angle = 30° impinges on a straight wall. If the upstream flow properties are M₁ = 2.8, p₁ = 1 atm, and T₁ = 300 K, calculate the pressure, temperature, Mach number, and total pressure downstream of the reflected wave.