Chapter 17: Problem 165
Assuming you have a thermometer and a device to measure the speed of sound in a gas, explain how you can determine the mole fraction of helium in a mixture of helium gas and air.
Chapter 17: Problem 165
Assuming you have a thermometer and a device to measure the speed of sound in a gas, explain how you can determine the mole fraction of helium in a mixture of helium gas and air.
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Get started for freeAn aircraft flies with a Mach number \(\mathrm{Ma}_{1}=0.9\) at an altitude of \(7000 \mathrm{m}\) where the pressure is \(41.1 \mathrm{kPa}\) and the temperature is \(242.7 \mathrm{K}\). The diffuser at the engine inlet has an exit Mach number of \(\mathrm{Ma}_{2}=0.3 .\) For a mass flow rate of \(38 \mathrm{kg} / \mathrm{s},\) determine the static pressure rise across the diffuser and the exit area
How do oblique shocks occur? How do oblique shocks differ from normal shocks?
Helium enters a nozzle at \(0.6 \mathrm{MPa}, 560 \mathrm{K},\) and a velocity of \(120 \mathrm{m} / \mathrm{s}\). Assuming isentropic flow, determine the pressure and temperature of helium at a location where the velocity equals the speed of sound. What is the ratio of the area at this location to the entrance area?
For an ideal gas flowing through a normal shock, develop a relation for \(V_{2} / V_{1}\) in terms of \(k, \mathrm{Ma}_{1},\) and \(\mathrm{Ma}_{2}\).
Air at 25 psia, \(320^{\circ} \mathrm{F}\), and Mach number \(\mathrm{Ma}=0.7\) flows through a duct. Calculate the velocity and the stagnation pressure, temperature, and density of air
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