2.=Air enters a constant-area duct at Mach 3 and stagnation conditions 750 K and 1.3 MPa. Assume y1.4. In the duct it undergoes frictionless heating such that the exit Mach number is unity. Considertwo cases: (a) normal shock at the inlet of the duct and (b) shock-free supersonic heating. Determinethe stagnation temperature and pressure at the exit in each case. Is there any reason why the totalenergy transfer should differ (or be equal) in the two cases?

Step 1: Case (a): Normal shock at the inlet of the duct For this case, we have a normal shock at the…

Answered: 2. = Air enters a constant-area duct at…

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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I need help on 3bii and iv
I3
Solve the question 5, please.
For non-isentropic constant-area flow with stagnation temperature change the following relation was determined: Y 1 To _ ²(y + 1)M² (1 + ¹ Z ¹ M²) 2 TO (1+yM²)² It is possible to use the above equation and calculate the downstream Mach number without resorting to iteration for a flow where the upstream Mach number, as well as the upstream and downstream stagnation temperatures, are known. This is a common calculation for flows through engine combustors. Presuming the left side is a known quantity, show that the above equation can be directly solved as a quadratic in M² and which roots correspond to the subsonic/supersonic solution. Rewrite the equation as: aM4 + bM² + c = 0, and then M² = (−b ± √b² - 4ac)/2a. Determine the appropriate expressions for a, b, and c.
(b) Air flows through a cylindrical duct at a rate of 2.3 kg/s. Friction between air and the duct and friction within air can be neglected. The diameter of the duct is 10cm and the air temperature and pressure at the inlet are T₁ 450 K and P₁ = 200 kPa. If the Mach number at the exit is Ma2 determine the rate of heat transfer and the pressure difference across the duct. The constant pressure specific heat of air is cp = 1.005 kJ/kg-K. The gas constant of air is R = 0.287 kJ/kg-K and assume k = 1.4. -
1. Air flow isentropically through a converging nozzle attached to a reservoir, where the pressure is 170 kPa and temperature is 300 K. At the inlet to the nozzle the Mach number is 0.2, the nozzle discharge to the atmosphere (100kPa). The discharge area is 0.02 m?. Determine the magnitude and direction of the force that must be applied to hold the nozzle in place.
A flow of air with Mach number M1 = 2, pressure p1 = 0.7 atm, and temperature 630 degR is turned away from itself through an angle of 26.38 deg. Determine the Mach number, the staticpressure, the static temperature, and the stagnation pressure after the turn (all pressures in atm).Also determine the Mach angles at the beginning and end of the expansion fan.
Q1: when aircraft is ffying at subsonic velocity, the pressure at its nose i e. the stagnation point is found to be 160 kpa. if the ambient pressure and temperature are 100 kpa and 298k respectively, find the speed and Mach number at which the aircraft is flying.-
I need the answer as soon as possible
Air is flowing in a convergent nozzle. At a particular location within the nozzle the pressure is 280 kPa, the stream temperature is 345 K. and the velocity is 150 m/s. If the cross-sectional area at this location is 9.29 x 103 m², find: (a) The Mach number at this location, (b) The stagnation temperature and pressure. (c) The area, pressure, and temperature at the exit where M-1.0. (d) The mass rate of flow for the nozzle. Indicate any assumptions you may make and the source of data used in the solution.
Looking for correct solution
Qs: A two-dimensional supersonic inlet is to be designed to operate at Mach 2.4. Deceleration is to occur through a series of oblique shocks followed by a normal shock, as shown in Figure. Determine the loss of stagnation pressure for the cases of two, three, and four oblique shocks. Assume the wedge turning angles are each 6°. M. = 2.4 Vi, Pai P.- 50 kPa 12° Vi, Pai T.-0° C

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