Nitrogen flows from a large tank, through a convergent nozzle of 2-in. tip diameter, into the atmosphere. The temperature in the tank is 200°F. Calculate pressure, velocity, temperature, and sonic velocity in the jet, and calculate the flow rate when the tank pressure is (a) 30 psia and (b) 25 psia. Barometric pressure is 15.0 psia. What is the lowest tank pressure that will produce sonic velocity in the jet? What is this velocity, and what is the flowrate?
Want to see the full answer?
Check out a sample textbook solutionChapter 12 Solutions
Fox And Mcdonald's Introduction To Fluid Mechanics
Additional Engineering Textbook Solutions
Starting Out with Programming Logic and Design (5th Edition) (What's New in Computer Science)
Management Information Systems: Managing The Digital Firm (16th Edition)
Concepts Of Programming Languages
Electric Circuits. (11th Edition)
Mechanics of Materials (10th Edition)
Java How to Program, Early Objects (11th Edition) (Deitel: How to Program)
- Please Help with this question. Show clear steps and highlight the answers. Also explain the sub question related to the main question please. THanks!arrow_forwardThe stagnation chamber of a wind tunnel is connected to a high pressure air bottle farm which is outside the laboratory building. The two are connected by a long pipe which has a inside diameter of 4 inches. If the static pressure ratio between the bottle farm and the stagnation chamber is 10 and the bottle farm static pressure is 100 atm, how long can the pipe be without choking and what is the change in entropy? Assume adiabatic,subsonic, one-dimensional flow with a friction coefficient of 0.005.arrow_forwardAs shown in figure Q1, air flows through a converging nozzle from a large tank and into a receiver. At section 1, the temperature is 350 k, the pressure is 320 kPa (abs), and the flow the flow area is 0.40 m?. The pressure in the large tank is 360 kPa (abs). Nozzle exit area is 0.30 m?. Air flow is assumed to be steady and isentropic in the converging nozzle. Express answer at least 3 significant figures. Take K as 1.40 and R as 0.287 kJ/kg.K Determine: a) The mach number at Section 1. b) The mach number, pressure and velocity at the exit. c) The mass flow rate through the nozzle. Large Tank Pressure = 360 kPa (abs) Air flows Nozzle Exitarrow_forward
- The converging-diverging nozzle(as shown in the figure given below) expands and accelerates dry air to supersonic speeds at the exit where p2 = 8 kPa and T₂ = 240 K. At the throat, p₁ = 284 kPa, T₁= 665 K, and V₁ = 495 m/s. NOTE: This is a multi-part question. Once an answer is submitted, you will be unable to return to this part. Air- D₁ = 1 cm Kg/s D₂ = 2.5 cm Determine the mass flow for a steady compressible flow of an ideal gas.arrow_forwardQ.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C and a pressure of 500 kPa by a converging nozzle, as shown in Figure. Heat is lost at the rate of 250 kJ /kg. Determine the exit pressure and Mach number and the mass flow rate for a back pressure of 0 kPa. q = 250 kJ/kg Pr = 500 kPa Tr = 500°C Po = 0 kPa D= 0.02marrow_forwardAir at atmospheric pressure and at 25°C enters a centrifugal blower when the rotor is spinning at 900 rpm. The inner and outer diameters of the rotor are 50 cm and 60 cm, respectively. Air enters the rotor radially and makes angle of -68° with the wheel tangent at the exit. The flow rate expected is 1.8 m3/s. If the efficiency, based on stagnation enthalpy, is 88.1%, calculate the power input, efficiency based on static enthalpy, and the exit fluid angle. Ans: n= 55.7%; exit fluid angle = 270° Answer provided above please provide full solutionarrow_forward
- A wind tunnel nozzle is designed to yield a parallel uniform flow of air with a Mach number of 3.0. The stagnation pressure of the air supply reservoir is 7000 kPa, and the nozzle exhausts into the atmosphere (100 kPa). Calculate the flow angle at the exit lip of the nozzle. Ma-3.0 100 kPa 7000 kPa angle = ?arrow_forwardIn Fig. 1, the box-fan of weight 22 N is hovering in the air. The air approaches the blades from the top with a negligible velocity and leaves the blades at a uniform velocity at the atmospheric pressure. The diameter of the blade span area is 0.9 m. Determine (a) The air exit velocity to produce 22 N force.(b) The volume flow rate needed.(c) The minimum power that must be supplied to the airstream.Take the air density to be 1.25 kg/m3.arrow_forwardNeed step by step explanationarrow_forward
- a) A convergent-divergent nozzle with a given area ratio is supplied with air at a constant stagnation pressure P, and a constant stagnation temperature To. With the aid of sketches give a clear account of the operation of convergent-divergent nozzles as a function of back pressure P. In your answer clearly indicate the critical points (pressure ratios) along the pressure ratio axis. A rocket is equipped with a convergent-divergent nozzle (== 3.0). b) pare supply temperture and pressure of the Determine the design choked subsonic and supersonic Mach numbers for this area ratio. You may assume the combustion products have the same properties as air and the the nozzle is an ideal nozzle. c) Determine the range of pressure ratios for which a normal shock wave appears in the divergent part of the nozzle. d) At an altitude of 11 km what should be the supply pressure to the nozzle in order to have a fully expanded nozzle. What would be the nozzle's discharge mass flow rate per unit throat…arrow_forwardAir is stored in a tank of 2 m2 in volume at a pressure of 3 MPa and a temperature of 300 K. The gas is discharged through a converging nozzle with an exit cross-sectional area of 0.0012 m'. For a back pressure of 101 kPa, find the time required ·for the tank pressure to drop to 300 kPa. Assume quasi-steady flow through the nozzle, where the steady !low equations are applicable at each instant of time. Also assume that the temperature of the air in the tank Is constant.arrow_forwardAn industrial nozzle as shown in Figure 3 works with an inert gas rush through the nozzle where the speed of the gas at the nozzle throat is recorded equal to the speed of sound. The inlet velocity, temperature, and pressure are 98 m/s, 600 oC, and 88 psi, respectively.Take the property of inert gas for k = 1.66 and cp = 5.192 kJ/kg. K. Calculate:a) Stagnation pressureb) Mach number at the nozzle inletc) Temperature of the gas at the throatd) Pressure of the gas at the throatarrow_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