The wave angle, Mach number and temperature after shock.
Answer to Problem 72EP
The wave angle, Mach number and temperature after shock are
Explanation of Solution
Given:
Air pressure, air temperature and Mach number are
Concept used:
Relation of wave angle is expressed as follows:
Here, wave angle is
Relation of upstream normal Mach number is expressed as follows:
Here, wave weak angle is
Relation of downstream normal Mach number is expressed as follows:
Here, upstream normal Mach number is
Relation of the downstream Mach number is expressed as follows:
Here, wave weak angle is
Relation of downstream pressure is expressed as follows:
Here, downstream pressure is
Relation of downstream Temperature is expressed as follows:
Here, downstream pressure is
Calculation:
Substitute
Solve the above equation by iteration. We get two value of wave angle as
Substitute
Substitute
Substitute
Substitute
Substitute
Thus, the wave angle, Mach number and temperature after shock are
Conclusion:
The wave angle, Mach number and temperature after shock are
Want to see more full solutions like this?
Chapter 12 Solutions
Fluid Mechanics: Fundamentals and Applications
- Nitrogen 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_forwardHow is the Mach number of a flow defined? What does a Mach number of 2 indicate?arrow_forwardAir flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.6. If the pressure and temperature of air are 58 kPa and 270 K, respectively, upstream of the shock, calculate the pressure, temperature velocity, Mach number, and stagnation pressure downstream of the shock. Calculate the entropy changes of air and helium across the normal shock wavearrow_forward
- Consider subsonic Fanno flow of air with an inlet Mach number of 0.70. If the Mach number increases to 0.90 at the duct exit as a result of friction, will the (a) stagnation temperature T0, (b) stagnation pressure P0, and (c) entropy s of the fluid increase, decrease, or remain constant during this process?arrow_forwardIs it possible to accelerate a gas to a supersonic velocity in a converging nozzle? Explainarrow_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_forward
- How does the parameter Ma* differ from the Mach number Ma?arrow_forwardConsider the supersonic flow of air over a two-dimensional wedge with a half angle of 10 degrees at 70 kPa, 260 kelvin, and mach number 2.4 after shock. If the axis of the wedge is tilted 25 degrees beforehand, determine the post-shock Mach number, temperature and pressure on the wedge.arrow_forwardWhen an airplane is flying at a constant speed relative to the ground, is it correct to say that the Mach number of this airplane is also constant?arrow_forward
- Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.5. If the pressure and temperature of air are 10.0 psia and 440.5 R, respectively, upstream of the shock, calculate the pressure, temperature, velocity, Mach number, and stagnation pressure downstream of the shock. Compare these results to those for helium undergoing a normal shock under the same conditions.arrow_forwardAs an airplane flying with constant velocity moves from a cold air mass into a warm air mass, how does the Mach number change? increases decreases remains the samearrow_forwardAn 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_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