Fluid Mechanics: Fundamentals and Applications
4th Edition
ISBN: 9781259696534
Author: Yunus A. Cengel Dr., John M. Cimbala
Publisher: McGraw-Hill Education
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Chapter 12, Problem 96CP
To determine
Effect of friction on the flow velocity in subsonic and supersonic Fanno flow.
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Chapter 12 Solutions
Fluid Mechanics: Fundamentals and Applications
Ch. 12 - What is dynamic temperature?Ch. 12 - Calculate the stagnation temperature and pressure...Ch. 12 - Prob. 6PCh. 12 - Prob. 7PCh. 12 - Prob. 8EPCh. 12 - Prob. 9PCh. 12 - Products of combustion enter a gas turbine with a...Ch. 12 - Is it possible to accelerate a gas to a supersonic...Ch. 12 - Prob. 72EPCh. 12 - Prob. 73P
Ch. 12 - Prob. 74PCh. 12 - Prob. 75PCh. 12 - For an ideal gas flowing through a normal shock,...Ch. 12 - Prob. 77CPCh. 12 - On a T-s diagram of Raleigh flow, what do the...Ch. 12 - What is the effect of heat gain and heat toss on...Ch. 12 - Prob. 80CPCh. 12 - Prob. 81CPCh. 12 - Prob. 82CPCh. 12 - Argon gas enters a constant cross-sectional area...Ch. 12 - Prob. 84EPCh. 12 - Prob. 85PCh. 12 - Prob. 86PCh. 12 - Prob. 87EPCh. 12 - Prob. 88PCh. 12 - Prob. 89PCh. 12 - Prob. 90PCh. 12 - Prob. 91PCh. 12 - Prob. 93CPCh. 12 - Prob. 94CPCh. 12 - Prob. 95CPCh. 12 - Prob. 96CPCh. 12 - Prob. 97CPCh. 12 - Prob. 98CPCh. 12 - Prob. 99CPCh. 12 - Prob. 100CPCh. 12 - Prob. 101PCh. 12 - Air enters a 5-cm-diameter, 4-m-long adiabatic...Ch. 12 - Helium gas with k=1.667 enters a 6-in-diameter...Ch. 12 - Air enters a 12-cm-diameter adiabatic duct at...Ch. 12 - Prob. 105PCh. 12 - Air flows through a 6-in-diameter, 50-ft-long...Ch. 12 - Air in a room at T0=300k and P0=100kPa is drawn...Ch. 12 - Prob. 110PCh. 12 - Prob. 112PCh. 12 - Prob. 113PCh. 12 - Prob. 114PCh. 12 - Prob. 115PCh. 12 - Prob. 116EPCh. 12 - A subsonic airplane is flying at a 5000-m altitude...Ch. 12 - Prob. 118PCh. 12 - Prob. 119PCh. 12 - Prob. 120PCh. 12 - Prob. 121PCh. 12 - Prob. 122PCh. 12 - Prob. 123PCh. 12 - An aircraft flies with a Mach number Ma1=0.9 at an...Ch. 12 - Prob. 125PCh. 12 - Helium expands in a nozzle from 220 psia, 740 R,...Ch. 12 - Prob. 127PCh. 12 - Prob. 128PCh. 12 - Prob. 129PCh. 12 - Prob. 130PCh. 12 - Prob. 131PCh. 12 - Prob. 132PCh. 12 - Prob. 133PCh. 12 - Prob. 134PCh. 12 - Prob. 135PCh. 12 - Prob. 136PCh. 12 - Prob. 137PCh. 12 - Prob. 138PCh. 12 - Air is cooled as it flows through a 30-cm-diameter...Ch. 12 - Prob. 140PCh. 12 - Prob. 141PCh. 12 - Prob. 142PCh. 12 - Prob. 145PCh. 12 - Prob. 148PCh. 12 - Prob. 149PCh. 12 - Prob. 150PCh. 12 - Prob. 151PCh. 12 - Prob. 153PCh. 12 - Prob. 154PCh. 12 - Prob. 155PCh. 12 - Prob. 156PCh. 12 - Prob. 157PCh. 12 - Prob. 158PCh. 12 - Prob. 159PCh. 12 - Prob. 160PCh. 12 - Prob. 161PCh. 12 - Prob. 162PCh. 12 - Assuming you have a thermometer and a device to...
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- 1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. Consider the isentropic flow through a supersonic wind-tunnel nozzle. Thereservoir properties are T0 = 500 K and p0 = 10 atm. If p = 1 atm at thenozzle exit, calculate the exit temperature and density.arrow_forwardAir at 7.20 MPa (abs.) and a temperature 1100K flows isentropically through a converging-diverging nozzle, the throat area is 0.01 m^2. Determine:1- The downstream velocity, in the section where the Mach number is 4.0;2- The mass flow rate through the nozzlearrow_forward- Air at 200 kPa, 100°C, and Mach number Ma = 0.8 lows through a duct. Calculate the velocity and the stagnation pressure, temperature, and density of the air.arrow_forward
- Consider subsonic Fanno flow of air with an inlet Mach number of 0.70. If the Mach number increases to 0.90 at the duct exit as a result of friction, will the (a) stagnation temperature T0, (b) stagnation pressure P0, and (c) entropy s of the fluid increase, decrease, or remain constant during this process?arrow_forwardShock waves are treated as discontinuities here, but theyactually have a very small fi nite thickness. After giving itsome thought, sketch your idea of the distribution of gasvelocity, pressure, temperature, and entropy through theinside of a shock wave.arrow_forwardIs it possible to accelerate a fluid to supersonic velocities with a velocity other than the sonic velocity at the throat? Explainarrow_forward
- 21) Prove that for isentropic flow of perfect gas the effects of an area change on the flow properties (P,V,T,p) are opposite for subsonic and supersonic flow.arrow_forwardConsider supersonic airflow approaching the nose of a two-dimensional wedge at a Mach number of 3. Using Fig. , determine the minimum shock angle and the maximum deflection angle a straight oblique shock can have.arrow_forwardAn axial flow compressor stage has blade root, mean and tip velocities of 160, 200 and 240 m/s. The stage is to be designed for a stagnation temperature rise of 20k and an axial velocity of 160 m/s, both constant from root to tip. The work done factor is 0.93. Assuming 50% reaction at mean radius, calculate the stage air angles at root, mean and tip and the degree of reaction at the root and tip for a free vortex design.arrow_forward
- Consider subsonic Fanno flow accelerated to sonic velocity (Ma = 1) at the duct exit as a result of frictional effects. If the duct length is increased further, will the flow at the duct exit be supersonic, subsonic, or remain sonic? Will the mass flow rate of the fluid increase, decrease, or remain constant as a result of increasing the duct length?arrow_forward(a) Write Area-Velocity relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (b) Write Area-density relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (c) Write Area-Mach relation for compressible flows through a supersonic Convergent-Divergent nozzle What is the importance of it? (d) Plot the variation of density, pressure, temperature, velocity and Mach number for compressible flows through a supersonic Convergent-Divergent nozzle Note: Do NOT derive above relations.arrow_forwardQs: A two-dimensional supersonic inlet is to be designed to operate at Mach 2.4. Deceleration is to occur through a series of oblique shocks followed by a normal shock, as shown in Figure. Determine the loss of stagnation pressure for the cases of two, three, and four oblique shocks. Assume the wedge turning angles are each 6°. M. = 2.4 Vi, Pai P.- 50 kPa 12° Vi, Pai T.-0° Carrow_forward
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