The plot for mass flow parameter and Mach number.
Answer to Problem 119P
The plot for mass flow parameter and Mach number is
Explanation of Solution
Given information:
The Mach number varies from
Relation for mass flow parameter and Mach number.
Here, mass flow rate is
Calculation:
Substitute
Substitute
Table-(1) represents the value of flow rate parameter for different Mach numbers at specific heat ratio of
Table-(1)
| |
| |
| |
| |
| |
| |
| |
Substitute
Substitute
Table-(2) represents the value of flow rate parameter for different Mach numbers at specific heat ratio of
Table-(2)
| |
| |
| |
| |
| |
| |
| |
Substitute
Substitute
Table-(3) represents the value of flow rate parameter for different Mach number at specific heat ratio of
Table-(3)
| |
| |
| |
| |
| |
| |
| |
Figure-(1) represents the plot of flow rate parameter with Mach number for different value of specific heat ratio.
Figure-(1)
Want to see more full solutions like this?
Chapter 12 Solutions
Fluid Mechanics Fundamentals And Applications
- Air 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_forwardThe entropy increase across a normal shock wave is 199.5 J/(kg · K). Whatis the upstream Mach number?arrow_forwardNitrogen enters a converging–diverging nozzle at 800 kPa and 400 K with a negligible velocity. Determine the critical velocity, pressure, temperature, and density in the nozzle. Use data from the tables. The properties of nitrogen are k = 1.4 and R = 0.2968 kJ/kg·Karrow_forward
- Consider a hypersonic vehicle with a spherical nose flying at Mach 20at a standard altitude of 150,000 ft, where the ambient temperature andpressure are 500◦R and 3.06 lb/ft2, respectively. At the point on thesurface of the nose located 20◦ away from the stagnation point, estimatethe: (a) pressure, (b) temperature, (c) Mach number, and (d) velocity ofthe flow.arrow_forwardA gas at a specified stagnation temperature and pressure is accelerated to Ma = 2 in a converging–diverging nozzle and to Ma = 3 in another nozzle. What can you say about the pressures at the throats of these two nozzlesarrow_forwardA subsonic airplane is flying at a 5000-m altitude where the atmospheric conditions are 54 kPa and 256 K. A Pitot static probe measures the difference between the static and stagnation pressures to be 16 kPa. Calculate the speed of the airplane and the flight Mach number.arrow_forward
- A uniform supersonic flow of air at Mach 3.8, with a stagnation pressure of 5.0 MPa and stagnationtemperature of 1100 K, expands around a 23o convex corner. Determine the downstream Macharrow_forwardIf the exit Mach number in Fig. is 2.2, what is theexit area?(a) 0.10 m2, (b) 0.12 m2, (c) 0.15 m2, (d ) 0.18 m2, (e) 0.22 m2arrow_forwardConsider air entering a heated duct at p1 = 1 atm and T1 = 288 K. Ignore the effect of friction. Calculate the amount of heat per unit mass (in joules per kilogram) necessary to choke the flow at the exit of the duct for an inlet Mach number of M1 = 2.2.arrow_forward
- vortex generators on the upper surface of a wing will a. decrease the spanwise flow at high Mach numbers b. increase the critical Mach number c. decrease the intensity of the shockwave effects d. increase intensity of the shockwave effectsarrow_forwardThe Airbus A-340 passenger plane has a maximum takeoff weight of about 260,000 kg, a length of 64 m, a wing span of 60 m, a maximum cruising speed of 945 km/h, a seating capacity of 271 passengers, a maximum cruising altitude of 14,000 m, and a maximum range of 12,000 km. The air temperature at the crusing altitude is about −60°C. Determine the Mach number of this plane for the stated limiting conditions.arrow_forwardThe flow just upstream of a normal shock wave is given by p1 = 1 atm,T1 = 288 K, and M1 = 2.6. Calculate the following properties justdownstream of the shock: p2, T2, ρ2, M2, p0,2, T0,2, and the change inentropy across the shock.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