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 145P
To determine
An expression for the stagnation pressure ratio after a shock wave to the static pressure before the shock wave as a function of
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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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- Rewrite dV/V in terms of only Mach number and γ for a steady, adiabatic flow. Showall steps of the derivation clearly. γ = 1.4, R=287 J/kgKarrow_forwardA normal shock occurs in a stream of oxygen. The oxygen flows at Ma=1.8 and the upstream pressure and temperature are 40 psia and 85 degrees Fahrenheit. a) Calculate the following on the downstream side of the shock: static pressure, stagnation pressure, static temperature, stagnation temperature, static density, and velocity. b)If the Mach number is doubled to 3.6, what will be the resulting values of the parameters listed in part (a)?arrow_forwardThe entropy increase across a normal shock wave is 199.5 J/(kg · K). What is the upstream Mach number?PLease show step by step solns for better understanding thank you!arrow_forward
- What is the Mach Number of an air with a velocity of 250 m/s, at a temperature at 2800 meters?arrow_forward= 1.2 bar, and M1 = 3.0. An 2- Conditions before a shock are T1 = 40°C, pl oblique shock is observed at 45° to the approaching air flow. (a) Determine the Mach number and flow direction after the shock. (b) What are the temperature and pressure after the shock?arrow_forwardaircraft flies at the same Mach number but 50 m/s slower at 8 km compared to its speed at sea level. Find this Mach number a. 1.45 b. 1.55 c. 2.25 d. 1.65 e. 2.50.arrow_forward
- i need the answer quicklyarrow_forwardConsider a point in an airflow where the local Mach number, static pressure, and static temperature are 2.5, 0.3 atm, and 180 K, respectively. Calculate the local values of P0, T0, T ∗, a∗, and M∗ at this pointarrow_forward4. Determine the upstream Mach number, considering an oblique shock wave with ew = 32° and a pressure ratio, P2/P1 = 3.0.arrow_forward
- The propagation of disturbances from a point source that results in an oblique shock wave can be visualized in Figure Q2(b). From the diagram, derive the equation that relates Mach angle with the local Mach number.arrow_forwardA supersonic aircraft flies with a velocity lower by 39 m-s at 7800 m elevation, (T = - 54 C° at 7800 m) and (T = - 57 C° at 8800 m, M = 2), determine the difference between Mach no.s.arrow_forward2. Carbon dioxide gas (CO2) flows adiabatically along a duct. At station 1 the static pressure P₁=120 kPa and the static temperature T1= 120 oC. At station 2 further along the duct the static pressurep2=75 kPa and the velocity C 2= 150 m/s.Determine (1) the Mach number M 2 (2) the stagnation pressure poz (3) stagnationtemperature Toz (4) the Mach number M 1 For CO 2 take R = 188 J/(kg K) and K = 1.30.arrow_forward
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