Fundamentals Of Gas Dynamics 2nd Edition V. Babu - Solutions

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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 actually represent.
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 in terms of an arbitrary diameter.
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 2, we find that $p_{2}=45 \mathrm{psia}$ and $T_{2}=90^{\circ} \mathrm{F}$. Determine the
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 steam leaves the turbine with an enthalpy of $995 \mathrm{Btu} / \mathrm{lbm}$ and a velocity of
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 circulates around the cylinders at the rate of $25 \mathrm{lbm} /$ $\mathrm{min}$. The water enters
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 negligible.(b) Compute the flow rate if the final duct size is $10 \mathrm{~cm}$ in diameter.
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 diameter has increased to 6 in., the pressure is 45 psia. Assuming the flow to be isothermal, compute
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 temperature is $280 \mathrm{~K}$. If $1.4 \times 10^{4} \mathrm{~J} / \mathrm{kg}$ of heat is lost by
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 work or heat transfer takes place. The temperature at the exit, where the area is \(0.15
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 $500 \mathrm{ft} / \mathrm{sec}$. At a downstream section, $h_{2}=2240 \mathrm{Btu} / \mathrm{lbm}$
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 potential of $10 \mathrm{ft}$ with respect to the other connections shown in Figure P2.14. Steam enters
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 $u_{2}=1.340$ $\mathrm{MJ} / \mathrm{kg}$ and $ho=10 \mathrm{~kg} / \mathrm{m}^{3}$, calculate the work if
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 velocity of $85 \mathrm{~m} / \mathrm{s}$. Assuming isentropic operation, determine the exit static
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, determine the power required per unit mass flow rate of air. Also, determine whether the compression
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 and the static temperature at the exit.
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 added to cause the exit Mach number to be unity.
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 operation.
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 in the freestream, the static pressure and temperature are $26.5 \mathrm{kPa}$ and $223
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 chamber Nozzle
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 downstream of the shock?
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 downstream of the wave is tripled, what are the shock speed and the absolute velocity of the air
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 just ahead of the intake. Determine the stagnation pressure, static pressure, and temperature of the
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 the speed of the blast wave in the laboratory frame of reference and the stagnation temperature behind
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 laboratory frame of reference.
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 stationary frame of reference) in the region through which the shock has passed.
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 of the bullet, in the nose region, normal shock relationships can be used. Also note that the nose
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 that the fluid in the stream tube captured by the probe has passed through a normal shock wave. It is
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) $2000 \mathrm{~kJ} / \mathrm{kg}$. Also determine the ratio of mass flow rates between the two
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 mass flow rate, (b) the exit properties and (c) amount of heat to be added to cause the exit Mach
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. Determine the fuel-air ratio (on a mass basis) that will result in the exit Mach number being equal
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 air in the pipe.If the heat added is 450 kJ/kg, calculate (a) the inlet and exit Mach numbers,

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Fundamentals Of Gas Dynamics 2nd Edition V. Babu - Solutions

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