02: The large compressed-air tank shown in the figure bellow exhausts from a nozzle at an exit velocity of V 235 m/s. Assuming isentropic flow, compute: a) the exit Mach number. b) the pressure in the tank. (take; k = 1.396, C, = 917 J/Kg.k and R = 260 J/Kg.k) air at 30 "C tank conditions

02: The large compressed-air tank shown in the figure bellow exhausts from a nozzle at an exit velocity of V 235 m/s. Assuming isentropic flow, compute: a) the exit Mach number. b) the pressure in the tank. (take; k = 1.396, C, = 917 J/Kg.k and R = 260 J/Kg.k) air at 30 "C tank conditions

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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Problem 6: A constant-area frictionless pipe is thermally choked. The inlet total temperature and the heat flux are T1 = 650°R and q = 500 BTU/lbm, respectively. Calculate a) the inlet Mach number M1 b) exit total temperature T2 Cp = 0.24 BTUlbm'R, y = 1.4
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b) In a converging-diverging duct the flow conditions are such that a normal shock is formed at the exit of the diverging section. Upstream of the shock the flow conditions are as below. Mach number= '5.198', Pressure= '311886.9' Pa and Temperature= '228.72' K. Obtain the Mach number, pressure, and temperature at the downstream of the shock. Assume standard air properties (y=1.4).
Question 3.) We want to create a converging nozzle. The nozzle will be connected to a shop compressed air system through a tank. The requirement for the nozzle inlet area is A₁ = 20 cm² and the requirement for the nozzle exit area is A₂ = 5 cm². We want to find the air tank pressure, inlet Mach number, and standard volume flow rate for the different exit Mach numbers listed below: (Assume air inside tank has negligible velocity, temperature of the air inside the tank is 288 Kelvin, the nozzle exhausts to standard conditions Pb = 101 kilopascals): (a) Me = 0.3 (b) Me = 0.5 (c) Me = 1.0 Note: the standard volume flow rate (Q = m/p) assumes the density of the air is standard with p = 1.23kg/m³
b) In a converging-diverging duct the flow conditions are such that a normal shock is formed at the exit of the diverging section. Upstream of the shock the flow conditions are as below. Mach number= '0.5198', Pressure= '311886.9' Pa and Temperature= '228.72' K. Obtain the Mach number, pressure, and temperature at the downstream of the shock. Assume standard air properties (y=1.4).
AERODYNAMICS 1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle of 40° with the flow direction, is attached to the wedge. If the static pressure and temperature in the freestream are 0.5 Pa and 0°C, determine: a. the deflection angle in degrees b. the pressure ratio c. the Mach number in the downstream region
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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).
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