A convergent-divergent nozzle of 50-mm tip diameter discharges to the atmosphere (103.2 kPa) from a tank in which air is maintained at an absolute pressure and temperature of 690 kPa and 37.8°C, respectively. What is the maximum mass flow rate that can occur through this nozzle? What throat diameter must be provided to produce this mass flow rate?
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
INTERNATIONAL EDITION---Engineering Mechanics: Statics, 14th edition (SI unit)
Applied Statics and Strength of Materials (6th Edition)
Engineering Mechanics: Dynamics (14th Edition)
Automotive Technology: Principles, Diagnosis, And Service (6th Edition) (halderman Automotive Series)
Fundamentals Of Thermodynamics
Introduction To Finite Element Analysis And Design
- A high-pressure air reservoir is connected to the inlet of a convergent-divergent nozzle with an exit to throat area ratio of 2.0. The reservoir pressure is 1 atm (at standard sea level conditions). The exit pressure is 0.80 atm. Assume isentropic flow (except for the possibility of a normal shock inside the nozzle). If a pitot tube is inserted at a cross section which is 1.10 times the throat arca in the diverging section, what is the pressure that lthe pilul tube reads?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_forwardUpstream of the throat of an isentropic converging-diverging nozzle at section (1), V₁ = 150 m/s, P1 = 100 kPa (abs), T₁ = 20°C. If the discharge flow is supersonic and the throat area is 0.10 m², determine the mass flowrate in kg/s for the flow of air. kg/s m = iarrow_forward
- The converging-diverging nozzle of the engine of a new supersonic unmanned aerial vehicle (UAV) has an exit area of 50 cm^2 . At the design operating condition, the mass flow rate of exhaust gases (? ≈ 1.4, molecular weight = 26 g/mol) is 1.75 kg/s. The exhaust gases enter the nozzle with stagnation pressure and temperature equal to Po = 300 kPa and To = 500 K, respectively a) What is the optimal cruising altitude for the operation of the nozzle of this UAV? (b) What is the lowest altitude at which the plane can fly such that the flow inside the diverging part of the nozzle is kept supersonic? Note: - Assume that the stagnation conditions of the flow of exhaust gases entering the nozzle are kept constant with varying altitudearrow_forwardThe 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_forwardAir enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The throat area is one-half that of the discharge of the divergent section. Assuming the Mach number in the throat is 0.75. a. What are the values of the following quantities at the throat: pressure(atm), temperature(K), linear velocity(m/s), density(kg/m3), and mass velocity(kg/m2s)? b. What are the values of p*(in atm), T*(in K), u*(in m/s), and G* (in kg/m2.s) corresponding to reservoir conditions?arrow_forward
- Question A1 A converging-diverging nozzle has a throat area of 0.002 m? and an exit area of 0.0077 m?. The upstream air reservoir has stagnation pressure and temperature conditions: po=1000 kPa and To=500 K. The gas constant for air is 287 J/ kg K and its ratio of specific heats is 1.4. What is mass flow rate out of this nozzle when it operates in choked flow conditions?arrow_forwardA converging nozzle with a circular cross-section processing air steadily has a side profile as shown below. The diameter varies linearly with the axial length of 3 feet. Inlet and exit diameters of the nozzle are 1.5 and 1 feet, respectively, while inlet velocity is 100 ft/s. Determine: a) the flow velocity at the half-length and full length assuming incompressible flow, and b) the flow velocity at the half-length and full length assuming isentropic flow. For this part assume inlet flow conditions that mimic 10,000 ft altitude. 100 ft/s air 1.5 ft 3 ft 1 ftarrow_forwardAir flowing isentropically through a converging nozzle discharges to the atmosphere at standard sea level conditions. At the section where the absolute pressure is 179 kPa, the temperature is 39˚C and the air speed is 177 m/s. Determine the nozzle throat pressure.arrow_forward
- Determine the arcing distance of sprinkling installation. Overpressure in chamber A,from which water outflows by nozzles B, is ppA = 80 kPa. Velocity coefficient ofnozzles consider to be Ø = 0.90. Calculate the arcing distance in variants, for angle Ø(inclination of nozzle axis from horizontal line) being 35°, 45°and 55°.arrow_forwardAir enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The throat area is one-half that of the discharge of the divergent section. Assuming the Mach number in the throat is 0.75, what are the values of the following quantities at the throat: pressure(atm), temperature(K), linear velocity(m/s), density(kg/m3), and mass velocity(kg/m2s)?arrow_forwardAir enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The throat area is one-half that of the discharge of the divergent section. Assuming the Mach number in the throat is 0.75, what are the values of the following quantities at the throat: pressure(atm), temperature(K), linear velocity(m/s), density(kg/m3), and mass velocity(kg/m2s)? What are the values of p*(in atm), T*(in K), u*(in m/s), and G* (in kg/m2.s) corresponding to reservoir conditions? Write your answers according to order of properties asked.arrow_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