Answered: Design a rocket nozzle, knowing that…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question 3: a) In a '72.77' mm diameter pipeline conveying air, the inlet Mach number is measured to be $0.5198'. Find the length of the pipeline at which the flow conditions become sonic. Assume standard air properties and the average friction factor obtained from independent tests is 0.02. Also obtain Mach number at 1 m from the inlet of the pipe.
A fan manufacturer rates his fans at 152 mm water gage static pressure for 10 m of air per second at 21°C, 1,200 rpm and static efficiency of 69%. At what speed, in RPM, would these fans operate to develop 130 mm water gage when the temperature is 316°C? (14) O 1470 O 1670 O 1770 1870 1570
An air compressor delivers 10 ft^3 of air at a pressure of 130 psia and 85°F into an air reservoir. Calculate the mass of air delivered (Ibm)
[1] In the cold climates, water pipes may freeze and burst if proper precautions are not taken. In such an occurrence, the exposed part of a pipe on the ground ruptures, and water shoots up to 34 m. Estimate the gage pressure of water in the pipe.
5. For the subsonic axial-flow air expander specified, calculate the stagnation and static pressures and temperatures and the Mach number at the rotor-inlet plane (figure P2.5). Also find the rotor rotational speed and the nozzle-inlet blade height for constant-outer-diameter blading. Sketch the form of the complete turbine expansion on an enthalpy-entropy chart. The axial velocity will be constant at this design point. Mass flow, m = 2 kg/s Nozzle-inlet stagnation temperature, Tuni = 400 °C. Absolute nozzle-inlet stagnation pressure, Po,ni = 3 bars(= 3 x 105 N/m²) Mean diameter, dm = 0.25 m. Blade height at rotor entry, 1 = 0.1dm(= 1/2[ds - dn]). Flow angle at nozzle exit, a₁ = 70° to axial direction. Drop in stagnation pressure in nozzle, Apo = 0.05 bar Rotor peripheral speed at mean diameter, um = 0.5x (component of nozzle outlet velocity, Ce,1).
a turbojet on a test stand air at inlet has density of 1.1 kg/m^3 at the exit gas has higher velocity and higher temp, but pressure is the same. inlet area is 0.5m^2 and free stream velocty is 200m/s. fuel air mix is 1:15 at exit, engine area is 0.3m^2, gas velocity 800m/s Determine the density of gas at exit and evaluate reaction forces to hold test stand Turbojet Engine V1 V2 P2 A1 A2 Test Stand
The power output of a steam turbine is 5 MW. The inlet conditions are 2 MPa of pressure, 400 degrees * C of temperature, 50 m/s of velocity and 10 m of elevation. The exit conditions are 15 kPa, 0.9 dry quality, 180 m/s and 6 m elevation. Compute: (i) The magnitude of A h, A ke, Ape, (ii) Work done per kg of steam,
Q4) The nozzles receive steam at 1.75 MPa, 300 °C, and exit pressure of steam is 1.05 MPa. If there are 16 nozzles, find the cross-sectional area of the exit of each nozzle for a total discharge to be 280 kg/min. Assume nozzle efficiency of 90%. If the steam has velocity of 120 m/s at the entry to the nozzles, by how much would the discharge be increased?
Calculate the thrust of a turbojet engine with an inlet diameter of 4 ft. If an airplane is flying at altitude of 15km at Mach 0.8 with an exit velocity of 900ft/s. The turbojet engine thrust at 15-km. (in Lbf)

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Design a rocket nozzle, knowing that you have a chamber pressure of 6.28 MPa, mass flow rate of 1.23, and temperature of 825K.