The maximum theoretical flow rate (slug/s) through a supersonic nozzle is
where At(ft2) is the nozzle throat area, p0 (psia) is the tank pressure, and T0(R) is the tank temperature. Is this equation dimensionally correct? If not, find the units of the 2.38 term. Write the equivalent equation in SI units.
Want to see the full answer?
Check out a sample textbook solutionChapter 1 Solutions
Fox And Mcdonald's Introduction To Fluid Mechanics
Additional Engineering Textbook Solutions
Statics and Mechanics of Materials (5th Edition)
Applied Statics and Strength of Materials (6th Edition)
Engineering Mechanics: Statics
Thinking Like an Engineer: An Active Learning Approach (3rd Edition)
Introduction To Finite Element Analysis And Design
Degarmo's Materials And Processes In Manufacturing
- A jet fighter plane travels in horizontal flight at Mach 1.20 (that is, 1.20 times the speed of sound in air). At the instant an observer on the ground hears the shock wave, what is the angle her line of sight makes with the horizontal as she looks at the plane?arrow_forwardA belt moves upward at velocity V, dragging a fi lm ofviscous liquid of thickness h , as in Fig. . Near the belt,the fi lm moves upward due to no slip. At its outer edge, thefi lm moves downward due to gravity. Assuming thatthe only nonzero velocity is υ ( x ), with zero shear stress atthe outer fi lm edge, derive a formula for ( a ) υ ( x ), ( b ) the average velocity V avg in the fi lm, and ( c ) the velocity V c forwhich there is no net flow either up or down. ( d ) Sketchυ ( x ) for case ( c ).arrow_forward3. The NASA X-43 flies at a Mach number of 9.4 at an altitude of 30,000 m, where thepressure is 1171.8 Pa and the temperature is 226 K. If a supersonic wind tunnel isdesigned to reproduce these conditions, calculate the following:(a) The velocity (m/s), total/stagnation temperature (K), and total/stagnation pres-sure (kPa) in the test section.(b) The velocity (m/s), total temperature (K), and total pressure (kPa) behind thenormal shock formed in front of a blunt surface in the test section.(c) The change in entropy across this normal shock.arrow_forward
- Water at 20◦C flows along the streamlines shown in Figure3.11. The (gauge) pressure, velocity, and elevation at Point1 are 15.0 kPa, 1.0 m/s, and 5.02 m, respectively, and thevelocity and elevation at Point 2 are 0.5 m/s and 5.21 m,respectively. Estimate the pressure at Point 2. The given answer was P2 = 13.5 kPa. Show detailed solution pls thank you.arrow_forwardConsider the inviscid, incompressible flow of air along a streamline. The air density along the streamline is 0.002377 slug/ft3, which is standard atmospheric density at sea level. At point 1 on the streamline, the pressure and velocity are 2116 lb/ft2 and 10 ft/s, respectively.Further downstream, at point 2 on the streamline, the velocity is 190 ft/s. Calculate the pressure at point 2. What can you say about the relative change in pressure from point 1 to point 2 compared to the corresponding change in velocity?arrow_forwardBy an inkjet printerthe diameter (d) of the points created, the dynamic of the inkviscosity (µ), density (ρ), surface tension (σ), nozzlediameter (D), the distance of the nozzle from the paper surface (L) andink jet velocity is thought to depend on V.Get an expression to characterize the behavior of the ink jetplease.arrow_forward
- The airfl ow underneath an air hockey puck is very complex,especially since the air jets from the air hockey tableimpinge on the underside of the puck at various points nonsymmetrically.A reasonable approximation is that at anygiven time, the gage pressure on the bottom of the puck ishalfway between zero (atmospheric pressure) and the stagnationpressure of the impinging jets. (Stagnation pressureis defined as p0 =1/2ρV2jet . ) ( a ) Find the jet velocity V jetrequired to support an air hockey puck of weight W anddiameter d . Give your answer in terms of W , d , and thedensity ρ of the air. ( b ) For W = 0.05 lbf and d = 2.5 in,estimate the required jet velocity in ft/s.arrow_forwardFor a flow in the xy plane, the x component of the velocity is given as u=3x2y-y3. Determine the y component for steady state and incompressible flow. Does this result also apply to unstable, incompressible flow? Why is that? How many possible y components are there? Discuss.arrow_forwardSuppose an aircraft is flying at standard sea-level at M = 0.8 and using a pitot-static tube for airspeed measurement. Determine the actual difference in total and static pressures as would be measured by the pitot-static system. Compare the speed of the aircraft as determined using the actual pressure difference and incompressible flow versus that knowing the actual Mach number. Use k = 1.4.arrow_forward
- A bicycle tire is fi lled with air at an absolute pressure of169.12 kPa, and the temperature inside is 30.0 °C. Supposethe valve breaks, and the air starts to exhaust out of the tireinto the atmosphere (pa = 100 kPa absolute and Ta =20.0 °C). The valve exit is 2.00 mm in diameter and is thesmallest cross-sectional area of the entire system. Frictionallosses can be ignored here; one-dimensional isentropicflow is a reasonable assumption. (a) Find the Machnumber, velocity, and temperature at the exit plane of thevalve (initially). (b) Find the initial mass flow rate out ofthe tire. (c) Estimate the velocity at the exit plane using theincompressible Bernoulli equation. How well does thisestimate agree with the “exact” answer of part (a)? Explain.arrow_forwardAn airplane approaches at an altitude of 10 km flying at 600 km/hr. 1. What would you hear, and when would you hear it, if the plane were "hypersonic", traveling three times the speed of sound, or "Mach 3"? That's approximately the fastest military aircraft in routine service today. note: To have higher speeds in the air takes considerably more energy. For example, after two and half minutes of flight, when the first-stage main engines of the Space X Falcon shut down, it is 80 kilometers high and moving at Mach 10 on its way to Earth orbit. The Mach number depends on the temperature of the air.arrow_forwardIf Reynolds number relate the inertial and viscous forces, which of the following relates the inertial andgravitational forces?A. Froude NumberB. Weber NumberC. Galileo NumberD. Eotvos Numberarrow_forward
- Elements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
- Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY