1. Find the pressure of air at a point in a stream where M equals 1.8 when thepressure and Mach number at another point in the stream are 25 psia and 0.8respectively. Assume isentropic conditions.2. Air having a reservoir pressure of 30 psia and density of 0.15 lb/ft isaccelerated to a Mach number of 1.6. Find the static pressure, density, andtemperature at this Mach number.3. Consider the flow of air through a supersonic nozzle. The reservoir pressureand temperature are 5 atm and 500 K, respectively. If the Mach number at thenozzle exit is 3, calculate the exit pressure , temperature, and density.4. A supersonic nozzle is a convergent-divergent duct , which is fed by a largereservoir at the inlet to the nozzle. In the reservoir of the nozzle, the pressureand temperature are 10atm and 550°R , respectively. At the nozzle exit, thepressure is 1 atm. Calculate the temperature and density of the flow at the exit.Assume the flow is isentropic and , of course, compressible.5. The mass flow of air through a supersonic nozzle is 1.5 lbm/s. The exitvelocity is 1,500 ft/sec, and the reservoir temperature and pressure are 1,000'R and 7 atm , respectively. Calculate the area of the nozzle exit.

Stagnation pressure will remain same. Stagnation pressure formula Po =P (1+(r-1/r)M2 )(r/r-1)

Answered: 1. Find the pressure of air at a point…

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.

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

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Question

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. The mass flow of air through a supersonic nozzle is 1.5 lbm/s. The exit
velocity is 1,500 ft/sec, and the reservoir temperature and pressure are 1,000
'R and 7 atm , respectively. Calculate the area of the nozzle exit.

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