n aircraft is flying at an altitude of 12000 metres (T=216.65 K. p = 0.193 bar) at a Mach number of 0.82.The cross sectional area of the inlet diffuser before the L.P. compressor stage is 0.5 m. Determine(a) the mass of air entering the compressor per second (b) the speed of the aircraft (c) the stagnation%3Dpressure and temperature of air at the diffuser entry.

Answered: Image /qna-images/answer/0b1b0e0a-d399-46fc-af33-86feb18110da.jpg

Answered: n aircraft is flying at an altitude of…

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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5. An experimental centrifugal compressor is fitted with free-vortex guide vanes in order to reduce the relative air speed at inlet to the impeller. At the outer radius of the eye. air leaving the guide-vanes has a velocity of 91.5 m/s at 20 deg to the axial direction. Determine the inlet relative Mach number, assuming frictionless flow through the guide vanes, and the impeller total-to-total efficiency. Other details of the compressor and its operating conditions are: Impeller entry tip diameter. 0.457 m Impeller exit tip diameter. 0.762 m Slip factor 0.9 Radial component of velocity at impeller exit. 53.4m/s Rotational speed of impeller. 11 000 rev/min Static pressure at impeller exit. 223 kPa (abs.)
Solve the question, immediately.
A subsonic airplane is flying at a 5000-m altitude where the atmospheric conditions are 54 kPa and 256 K. A Pitot static probe measures the difference between the static and stagnation pressures to be 16 kPa. Calculate the speed of the airplane and the flight Mach number.
A steady adiabatic flow of perfect gas occurs between sections 1 and 2 of a duct. The Mach numbers at the two sections are equal, but the area at 2 is 4/3 times as large as the area at 1. What is the ratio of stagnation pressures of 2 to 1? is the process is reversible? 0.75 Yes 0.75 No 1.33 Yes 1.33 No
An ideal isentropic nozzle is attached to an infinite reservoir that has stagnation conditions 3 MPa and 2250 K, and a constant specific heat of 1.2. If the nozzle's static exit pressure is 38.871 kPa, what is the exit static temperature? Also determine the nozzle's exit Mach number, stagnation pressure, and stagnation temperature.
Air is cooled as it flows through a 30-cm-diameter duct. The inlet conditions are Ma1 = 1.2, T01 = 350 K, and P01 = 240 kPa and the exit Mach number is Ma2 = 2.0. Disregarding frictional effects, determine the rate of cooling of air.
An ideal gas is to flow isentropically from a large tank where the air is maintained at a temperature and pressure of 59 °F and 76 psia to standard atmospheric discharge conditions in a way to achieve a maximal velocity. Describe in general terms the kind of duct involved and determine the duct exit Mach number and velocity in ft/s if the gas is air. The problem can be solved either using the isentropic relations or this figure. The isentropic relations are more accurate, but difficult to use unless you code them into a computer program. (a) What is the pressure ratio for the flow? (b) Is the exit flow subsonic, sonic, or supersonic? (c) What is the exit Mach number? (a) Pexit/Po= i (b) (c) Mexit =
3. Air enters a converging-diverging nozzle at 1.50 MPa and 900 K with a negligible velocity. The flow is steady, one-dimensional, and isentropic with k =1.4. For an exit Mach number of Ma = 2.4 and a throat area of 15 cm2, determine (a) the T, P and p in the throat, (b) the T, P and p in the exit plane, including the exit area, and (c) the mass flow rate through the nozzle
Air enters a rectangular duct at T1 = 285 K, P1 = 390 kPa, and Ma1 = 2. Heat is transferred to the air in the amount of 55 kJ/kg as it flows through the duct. Disregarding frictional losses, determine the temperature and Mach number at the duct exit.
Air enters a diffuser with velocity 289.3m/sec and temperature T₁-300°K and exits with negligible velocity. Assume that air is an ideal gas with Cp=1.004 kJ/kg. Determine the temperature T₁ at the outlet of the diffuser. Provide your answer in Kelvin (K). 1
Consider air entering a heated duct at p1 = 1 atm and T1 = 288 K. Ignore the effect of friction. Calculate the amount of heat per unit mass (in joules per kilogram) necessary to choke the flow at the exit of the duct for an inlet Mach number of M1 = 2.2.
Air flows isentropically through a duct. At section 1, thepressure and temperature are 250 kPa and 125°C, andthe velocity is 200 m/s. At section 2, the area is 0.25 m2 andthe Mach number is 2.0. Determine (a) Ma1; (b) T2; (c) V2;and (d ) the mass fl ow.

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