The specific heat ratio at room temperature, k = 1.4. The universal gas constant is 8.314 kJ/kmol K and the air consists of 21% O2, 78% N2 and 1% Ar.(Assume the molar mass of O, N, and Ar atoms are 16 kg/kmol, 14 kg/kmol and 40 kg/kmol, respectively).Determine the speed of sound in air at (a) 450 K and (b) 1400 K.Determine the Mach number (Ma) of an object moving in air at a velocity of 270m/s for both cases.a) at 450 KSpeed of sound:m/sMach number:b) at 1400 KSpeed of sound:m/sMach number:

Given: Air at 450K and 1000 K V=270 m/s TO determine: Speed of sound and Mach number

Answered: Determine the speed of sound in air 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

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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.…
Solve for the ratio of the initial to final speed of sound if an air expands isentropically from 178.04 psia at 207°F to 65psia. Express your answer in 3 decimal places.
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.
Air at 50 Kpa, 300 K, and Mach 2.0 passes through a normal shock. Determine: a) Total temperature and pressure upstream of the shock b) Total temperature and pressure downstream of the shock. I bak
Air at sonic conditions and at static temperature and pressure of 340 K and 250 kPa, respectively, is to be accelerated to a Mach number of 1.6 by cooling it as it flows through a channel with constant cross-sectional area. Disregarding frictional effects, determine the required heat transfer from the air, in kJ/kg.
Q3/ 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.
An airship with a displacement volume of 2400 cu – m and total mass of 1.6 tonnes is released into the atmosphere with a polytropic index equal to 1.24. Assuming that the airship displacement volume does not change with altitude, determine (i) the temperature lapse rate of the atmosphere. (ii) the maximum height above sea level to which the aircraft can rise. NB: Atmospheric temperature and pressure at sea-level are 15°C and 101kPa, respectively. For air, the characteristics gas constant is equal to 287J/kg.
A supersonic aircraft flies at an altitude of 3000 m. An observer on the ground hears noise generated by the aircraft, which is 3000 m away horizontally, after 12 s. assume that the atmosphere is isothermal. Determine: (a) The Mach number of the aircraft. (b) The velocity of aircraft. (c) The distance traveled before the observer hears the noise, and (d) The temperature of the isothermal atmosphere.
I need the answer as soon as possible
The isentropic relation between different properties of flow can be written as:(in picture) By using the given equation and the isentropic flow relations, derivethe equations for the ratio of temperature, pressure,and densityin terms of Mach number.
The speed of a supersonic aircraft flying at an altitude of 1,100 meters corresponds to a Mach number of 2.5. Estimate the time elapsed, in seconds, between the instant the aircraft was directly over head of an observer and the instant the observer feels the disturbance due to the aircraft. Presume that the temperature at the given height is 280°K, with k = 1.4 and R = 2.87 J/kg·K, in determining the questions of the following three cases: A) When the observer is stationaryB) When the observer is moving in the direction of the aircraft at M = 0.5C) When the observer is moving in the opposite direction with M = 0.5.

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Determine the speed of sound in air at (a) 450 K and (b) 1400 K. Determine the Mach number (Ma) of an object moving in air at a velocity of 270m/s for both cases.