Pressure, temperature, velocity, Mach number, and stagnation pressure downstream of the shock and comparison of Helium undergoing the same shock.
Answer to Problem 74P
Downstream pressure
Downstream temperature
Downstream velocity
Downstream Mach number
Downstream stagnation pressure
Comparison with helium for the normal shock under same conditions we have
Downstream pressure
Downstream temperature
Downstream velocity
Downstream Mach number
Downstream stagnation pressure
Explanation of Solution
Given:
The upstream the shock is given by, Pressure of air
Temperature of air
Mach number
Calculation:
Downstream Mach number is given by
The properties of air are
Downstream pressure is given by the formula,
Downstream temperature is given by the formula,
Downstream velocity of speed is given by the formula,
Downstream stagnation pressure is given by formula,
Analysis for helium is to be found out,so we need to determine the downstream Mach number by the below formula
The properties of helium are
k = 1.667
Calculate for the downstream pressure for the helium gas given by the formula,
Calculate for the downstream temperature for the helium gas given by the formula,
Downstream velocity of speed is given by the formula,
Downstream stagnation pressure is given by formula,
Conclusion:
Therefore, we can concludeMach number and velocity are greater for helium than for air because of the different values of
Want to see more full solutions like this?
Chapter 12 Solutions
Fluid Mechanics: Fundamentals and Applications
- Ahead of the normal shock wave, the upstream pressure , temperature, and Mach number are 0.53 atm, 255 K, and 2.8, respectively. Determine the pressure downstream of the shock wave.arrow_forwardNitrogen enters a duct with varying flow area at 400 K, 100 kPa, and a Mach number of 0.3. Assuming a steady, isentropic flow, determine the temperature, pressure, and Mach number at a location where the flow area has been reduced by 20 percent.arrow_forwardNitrogen enters a converging–diverging nozzle at 620 kPa and 310 K with a negligible velocity, and it experiences a normal shock at a location where the Mach number is Ma = 3.0. Calculate the pressure, temperature, velocity, Mach number, and stagnation pressure downstream of the shock. Compare these results to those of air undergoing a normal shock at the same conditions.arrow_forward
- Air flowing at 8 psia, 480 R, and Ma1 = 2.0 is forced to undergo a compression turn of 15°. Determine the Mach number, pressure, and temperature of the air after the compression.arrow_forwardCarbon dioxide enters an adiabatic nozzle at 1200 K with a velocity of 50 m/s and leaves at 400 K. Assuming constant specific heats at room temperature, determine the Mach number (a) at the inlet and (b) at the exit of the nozzle. Assess the accuracy of the constant specific heat approximation.arrow_forwardMach number at a certain section in a diverging part of a c-d nozzle is 0.7. At farther section (towards the exit), Mach number reduces to 0.4. Hence, the cross-sectional area of the farther section is greater byarrow_forward
- An ideal isentropic nozzle is attached to an infinite reservoir that has stagnation conditions 3 MPa and 2250 K, and a constant specific heat of 1.2. If the nozzle's static exit pressure is 38.871 kPa, what is the exit static temperature? Also determine the nozzle's exit Mach number, stagnation pressure, and stagnation temperature.arrow_forwardCompressed air from the compressor of a gas turbine enters the combustion chamber at T1 = 700 K, P1 = 600 kPa, and Ma1 = 0.2 at a rate of 0.3 kg/s. Via combustion, heat is transferred to the air at a rate of 150 kJ/s as it flows through the duct with negligible friction. Determine the Mach number at the duct exit, and the drop in stagnation pressure P01 − P02 during this processarrow_forwardExample: Carbon dioxide flows steadily at a mass flow rate of 3 kg/s and pressure of 1400 kPa and 200°C with a low velocity. It expands after the nozzle to a pressure of 200 kPa. The duct is designed so that the flow can be approximated as isentropic. Determine the density, velocity, flow area, and Mach number at each location along the duct that corresponds to a pressure drop of 200 kPaarrow_forward
- An air stream with a Mach number of (3.04) a pressure of (302 kPa) and a temperature of (502 K) enters a diverging channel. If the ratio of the exit cross- sectional area to the inlet cross- sectional area is (3). Determine the back pressure which is necessary to produce a normal shock wave in the channel with a cross-sectional area equal to twice the inlet cross-sectional area. Assume steady, one-dimensional isentropic flow except through the normal shock wave. Ax=2Ai , Ae=3Aiarrow_forwardAir flowing at 32 kPa, 240 K, and Ma1 = 3.6 is forced to undergo an expansion turn of 15°. Determine the Mach number, pressure, and temperature of air after the expansion.arrow_forwardHow does the Mach number affect the behavior of compressible flow in a supersonic nozzle?arrow_forward
- Elements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
- Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY