QUESTION 8On a Mollier diagram show all the stagnation and static points required to represent thecomplete flow process in a diffuserAir enters a diffuser with an average velocity of 375 m/s at atemperature of 360 kPa and 470 K respectively and leaves at a stagnation pressure of 300 kPawith an average velocity of 120 m/s and a static pressure of 280 kPa.stagnation pressure andDetermine(i) The static pressure and Mach number of the air at inlet(ii)The diffuser efficiency,(iii)The Mach number at exit and the overall entropy increase.

Given Information :Inlet velocity of the diffuser is V1 = 375 m/sStagnation pressure at the inlet…

Answered: QUESTION 8 On a Mollier diagram show…

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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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).
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 × 10° N/m² and 0°C, determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge angle.
Fluid moves through a nozzle with Mach number of 1.5. Determine the following: (i) Speed of the fluid if the speed of sound in air is 325 m/s; (ii) Mach number if the speed of the fluid is 125 m/s.
Compressible Flow and Propulsion 1. Determine the speed of sound in Argon at 120 °C. Molecular weight of Argon = 40 kg/kmol and y= 1.667. (Ro = 8314.5 J/kmol K) %3D [Ans. 369 m/s] 2. Calculate the Mach number corresponding to the following speeds at an am temperature of 15 °C. Rair = 287 J kg*K, 1 mph = 0.447 ms?. ent (a) National speed limit of 70 mph [Ans. 0.09] (b) A top speed of 230 mph attained by a Formula driver. [Ans. 0.3] 3. Calculate the speed of an aircraft cruising in 20°C air where the angle of the zone of silence is a. 10° to the direction of travel. [1946ms) b. 20° to the direction of travel. [943ms] c. 80° to the direction of travel. [60ms] d. What is the maximum expected angle for M = 1? 4. Calculate the speed of sound during the flight of an aircraft for the two conditions (a) when it is at a cruising altitude of 10,000 m and the outside temperature is-60 °C. (b) when it lands in a desert city at a temperature of 45 °C (c) If the Mach number during cruising condition…
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QUESTION 14 The fan of a turbofan engine is tested at high speed. The flow approaches the fan tip at a relative Mach number M1rel = 1.19. An oblique shock forms at the fan tip leading edge, with a shock angle B = 87 degrees. Use cold-air- standard assumptions and the two-dimensional oblique shock formulae to determine the relative Mach number M2rel after the shock. State your answer to two decimal places. Partial credit is awarded for a reasonable approximation to the correct numerical answer. %3D
Question B2 a) At a given instant of time, two pressure waves, each moving at the speed of sound, emitted by a point source moving with a constant velocity in a fluid in at rest are shown in figure QB2. Determine the Mach number involved and indicate with a sketch the instantaneous location of the point source. R=5 cm 12 cm Figure QB2 R=24 cm [8 Marks] b) The gas velocity across a normal shock wave decreases from 480 m/s to 160 m/s. If the pressure and density upstream of the shock are 62 kPa and 1.5 kg/m ³, find the pressure and density downstream of the shock and the specific heat ratio of the gas. c) An aircraft is in supersonic flight at 11 km altitude on a standard day. The true air speed of the plane is 695 m/s. Calculate the flight Mach number of the aircraft. A total head tube is attached to the plane is used to sense stagnation pressure which is converted to flight Mach number by an on-board computer. However, the computer programme has ignored the normal shock wave that…

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