Questions and Answers of Fundamentals Of Gas

Write the equation used to relate the material derivative of any mass-dependent property to the properties inside, and crossing the boundaries of, a control volume. State in words what the integrals
In a 10 -in.-diameter duct the mass average velocity of water is \(14 \mathrm{ft} / \mathrm{sec}\).(a) What is the average velocity if the diameter changes to 6 in.?(b) Express the average velocity
Nitrogen flows in a constant-area duct. Conditions at section 1 are as follows: \(p_{1}=\) \(200 \mathrm{psia}, T_{1}=90^{\circ} \mathrm{F}\), and \(V_{1}=10 \mathrm{ft} / \mathrm{sec}\). At section
Steam enters a turbine with an enthalpy of \(1600 \mathrm{Btu} / \mathrm{lbm}\) and a velocity of \(100 \mathrm{ft} /\) \(\mathrm{sec}\) at a flow rate of \(80,000 \mathrm{lbm} / \mathrm{hr}\). The
A flow of \(2.0 \mathrm{lbm} / \mathrm{sec}\) of air is compressed from \(14.7 \mathrm{psia}\) and \(60^{\circ} \mathrm{F}\) to \(200 \mathrm{psia}\) and \(150^{\circ} \mathrm{F}\). Cooling water
Hydrogen expands isentropically from 15 bar absolute and \(340 \mathrm{~K}\) to 3 bar absolute in a steady flow process without heat transfer.(a) Compute the final velocity if the initial velocity is
At a section where the diameter is \(4 \mathrm{in}\)., methane flows with a velocity of \(50 \mathrm{ft} / \mathrm{sec}\) and a pressure of \(85 \mathrm{psia}\). At a downstream section, where the
Carbon dioxide flows in a horizontal duct at 7 bar abs. and \(300 \mathrm{~K}\) with a velocity of \(10 \mathrm{~m} / \mathrm{s}\). At a downstream location the pressure is 3.5 bar abs. and the
Nitrogen, traveling at \(12 \mathrm{~m} / \mathrm{s}\) with a pressure of \(14 \mathrm{bar}\) abs. at a temperature of 800 \(\mathrm{K}\), enters a device with an area of \(0.05 \mathrm{~m}^{2}\). No
Hydrogen flows through a horizontal insulated duct. At section 1, the enthalpy is \(2400 \mathrm{Btu} / \mathrm{lbm}\), the density is \(0.5 \mathrm{lbm} / \mathrm{ft}^{3}\), and the velocity is
Cold water with an enthalpy of \(8 \mathrm{Btu} / \mathrm{lbm}\) enters a heater at the rate of \(5 \mathrm{lbm} / \mathrm{sec}\) with a velocity of \(10 \mathrm{ft} / \mathrm{sec}\) and at a
The control volume shown in Figure \(P 2.15\) has steady, incompressible flow, and all properties are uniform at the inlet and outlet. For \(u_{1}=1.256 \mathrm{MJ} / \mathrm{kg}\) and
Air enters the diffuser of an aircraft jet engine at a static pressure of $20 \mathrm{kPa}$ and static temperature $217 \mathrm{~K}$, and a Mach number of 0.9. The air leaves the diffuser with a
Air is compressed adiabatically in a compressor from a static pressure of 100 kPa to 2000 kPa. If the static temperature of the air at the inlet and exit of the compressor are 300K and 800 K,
Air enters a turbine at a static pressure of 2 MPa, 1400 K. It expands isentropically in the turbine to a pressure of 500 kPa. Determine the work developed by the turbine per unit mass flow rate of
Air at 100 kPa, 295K and moving at 710 m/s is decelerated isentropically to 250 m/s. Determine the final static temperature and static pressure.
Air enters a combustion chamber at 75 m/s, 150 kPa and 300 K. Heat addition in the combustor amounts to 900 kJ/kg. Compute (a) the mass flow rate, (b) the exit properties and (c) amount of heat to be
Air at 900K and negligible velocity enters the nozzle of an aircraft jet engine. If the flow is sonic at the nozzle exit, determine the exit static temperature and velocity. Assume adiabatic
Air expands isentropically in a rocket nozzle from P0 = 3.5MPa, T0 = 2700K to an ambient pressure of 100 kPa. Determine the exit velocity, Mach number, and static temperature.
Consider the capture stream tube of an aircraft engine cruising at Mach 0.8 at an altitude of $10 \mathrm{~km}$. The capture mass flow rate is $250 \mathrm{~kg} / \mathrm{s}$. At station 1 , which is
The ramjet engine shown in Fig. 2.4 does not have any moving parts. It operates at high supersonic Mach numbers $( Fuel injectors Diffuser Flameholder Fig. 2.4 Schematic of a ramjet engine Combustion
A shock wave advances into stagnant air at a pressure of 100 kPa and 300 K. If the static pressure downstream of the wave is tripled, what are the shock speed and the absolute velocity of the air
Repeat Problem 1 assuming the fluid to be helium instead of air.Problem 1A shock wave advances into stagnant air at a pressure of $100 \mathrm{kPa}$ and $300 \mathrm{~K}$. If the static pressure
Air at $2.5 \mathrm{kPa}, 221 \mathrm{~K}$ approaches the intake of a ramjet engine operating at an altitude of $25 \mathrm{~km}$. The Mach number is 3.0. For this Mach number, a normal shock stands
A blast wave passes through still air at $300 \mathrm{~K}$. The velocity of the air behind the wave is measured to be $180 \mathrm{~m} / \mathrm{s}$ in the laboratory frame of reference. Determine
A normal shock wave travels into still air at 300 K. If the static temperature of the air is increased by 50K as a result of the passage of the shock wave, determine the speed of the wave in the
A shock wave generated due to an explosion travels at a speed of 1.5 km/s into still air at 100 kPa and 300 K. Determine the velocity of the air, static, and stagnation quantities (with respect to a
A bullet travels through air (300 K, 100 kPa) at twice the speed of sound. Determine the temperature and pressure at the nose of the bullet. Note that although there will be a curved, bow shock ahead
A pitot tube is used to measure the Mach number $\left(M_{1}\right)$ of a supersonic flow as shown in the figure.Although a curved shock stands ahead of the probe, it is fairly accurate to assume
Air enters a constant area combustion chamber at $100 \mathrm{~m} / \mathrm{s}$ and $400 \mathrm{~K}$. Determine the exit conditions if the heat added is (a) $1000 \mathrm{~kJ} / \mathrm{kg}$ and (b)
Air enters a combustion chamber at $75 \mathrm{~m} / \mathrm{s}, 150 \mathrm{kPa}$ and $300 \mathrm{~K}$. Heat addition in the combustor amounts to $900 \mathrm{~kJ} / \mathrm{kg}$. Compute (a) the
Determine the inlet static conditions and the mass flow rate if the heat addition in the above combustor were $1400 \mathrm{~kJ} / \mathrm{kg}$.
Air enters the combustor of a scramjet engine at $M=2.5$ and $T_{0}=1500 \mathrm{~K}$ and $P_{0}=1 \mathrm{MPa}$. Kerosene with calorific value of $45 \mathrm{MJ} / \mathrm{kg}$ is used as the fuel.
Air flows from a large reservoir where the pressure and temperature are 200 kPa, 300K respectively, through a pipe of diameter 0.05m and exhausts into the atmosphere at 100 kPa. Heat is added to the

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