3. An air stream, which is traveling at a Mach number of 1.8, undergoes a normal shockwave. The stagnation pressure and temperature before the normal shock wave are 150kPa and 350 K, respectively. Determinea) the temperature and the pressure after the normal shock wave,b) the Mach number and the velocity after the normal shock wave andc) the stagnation temperature and pressure after the shock wave andd) the entropy change across the normal shock wave(Ans. a) 325.4 K, 94.3 kPa, b) 0.6165, 223 m/s, c) 350 K, 122.2 kPa, d) 59.55 J/kgK)

The objective of this question is to determine the temperature, pressure, Mach number, velocity,…

Answered: 3. An air stream, which is traveling at…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

Solve it pls.
Steam at 500 kPa and a quality of 90 percent occupied a rigid vessel of volume 0.3m'. Calculate the mass, internal energy, and enthalpy of the steam.
3. Water vapor enters a subsonic diffuser at a pressure of 70 kPa, 160°C and 180 m/s. The inlet to the diffuser is 100 cm². During passage through the diffuser the fluid velocity is reduced to 60 m/s, the pressure increases to 100 kPa, and the heat transfer to the surroundings is 0.6 kJ/kg. Determine (a) the final temperature, (b) the mass flow rate in kg/s, and (c) the outlet area in cm². P₁ = 0.7 bar T₁ = 160°C V₁ = 180 m/s (2) A₁ = 100 cm² Steam (1) Yout 0.6 kJ/kg) m2 V₂ = 60 m/s P2 = 1.0 bar
The ratio of stagnation temperature at the exit and entry of a combustion chamber is 3.75. If the pressure, temperature and flow Mach number at the exit are 2.5 bar, 1000°C and 0.9 respectively, determine (i) Mach number, pressure and temperature of the gas at entry, (ii) total heat supplied per kg of gas, and (iii) the maximum heat that can be supplied. Take y= 1.4 and C, = 1.2 kJ/kg K. [Ans. M1 = 0.255, p1 1.9 bar, T, = 391.4 K, Q = 1301.7 kJ/kg, Qmax 1315.82 kJ/kg]
1. Find the pressure of air at a point in a stream where M equals 1.8 when the pressure and Mach number at another point in the stream are 25 psia and 0.8 respectively. Assume isentropic conditions. 2. Air having a reservoir pressure of 30 psia and density of 0.15 lb/ft is accelerated to a Mach number of 1.6. Find the static pressure, density, and temperature at this Mach number. 3. Consider the flow of air through a supersonic nozzle. The reservoir pressure and temperature are 5 atm and 500 K, respectively. If the Mach number at the nozzle exit is 3, calculate the exit pressure , temperature, and density. 4. A supersonic nozzle is a convergent-divergent duct , which is fed by a large reservoir at the inlet to the nozzle. In the reservoir of the nozzle, the pressure and temperature are 10atm and 550°R , respectively. At the nozzle exit, the pressure is 1 atm. Calculate the temperature and density of the flow at the exit. Assume the flow is isentropic and , of course, compressible. 5.…
Mach 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 by
Air enters a nozzle at 200 KPa, 360 K and a velocity of 180 meter per second . Assuming isentropic or adiabatic flow, if the pressure and temperature of air at a location where the air velocity equals the speed of sound, the Mach number at the nozzle inlet is Blank 1. The properties of air are : k = 1.4; Cp = 1005 J/kg-K; R = 287 J/kg-K. ***EXPRESS YOUR ANSWER in TWO (2) DECIMAL PLACE and WITHOUT UNITS****
Ahead of the normal shock wave, the upstream pressure, temperature, and Mach number are O.53 atm, 255 K, and 2.8, respectively. Determine the Mach number downstream of the shock wave.
Steam at a temperature of 250°C has specific volume of 0.15436 m^3/kg. What is the specific entropy in kJ/kg-K?
A certain SSSF, adiabatic control volume with single inflow and outflow streams has mass flow rate m(dot) = 7.5 kg/sec, and a specific entropy increase from inflow to outflow, se-şi = + 1.6 kJ/(K*kg). Determine the time-rate-of-change, net, of the entropy of the universe (control volume plus surroundings).
I need answer within 20 minutes please please with my best wishes
The entropy (s) of steam at pressure P = 18 MPa and internal energy (u) = 1699.1 kJ/kg is approximately: O 5.1064 kJ/kg. K O 1.2343 kJ/kg. K O 3.8720 kJ/kg. K

SEE MORE QUESTIONS

Recommended textbooks for you

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Control Systems Engineering

Mechanical Engineering

ISBN:

9781118170519

Author:

Norman S. Nise

Publisher:

WILEY

Mechanics of Materials (MindTap Course List)

Mechanical Engineering

ISBN:

9781337093347

Author:

Barry J. Goodno, James M. Gere

Publisher:

Cengage Learning

Engineering Mechanics: Statics

Mechanical Engineering

ISBN:

9781118807330

Author:

James L. Meriam, L. G. Kraige, J. N. Bolton

Publisher:

WILEY

SEE MORE TEXTBOOKS