I need the answer as soon as possible 3. A stationary normal shock occurs in an air stream when the pressure, temperature and Machnumber are 80 kPa, 100°C and 1.8 respectively. Compare the magnitude of final density ofair for the shock compression with the density of air, if it is compressed isentropically betweenthe same pressure limits.[Ans. Pshock = 1.7623 kg/m², pisentropic = 1.87 kg/m³]%3D

Answered: A stationary normal shock occurs in an…

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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A supersonic airflow at Ma1 = 3.2 and p1 = 50 kPa undergoesa compression shock followed by an isentropic expansionturn. The flow deflection is 30° for each turn. ComputeMa2 and p2 if (a) the shock is followed by the expansionand (b) the expansion is followed by the shock.
In compressible flow, velocity measurements with a Pitot probe can be grossly in error if relations developed for incompressible flow are used. Therefore, it is essential that compressible flow relations be used when evaluating flow velocity from Pitot probe measurements. Consider supersonic flow of air through a channel. A probe inserted into the flow causes a shock wave to occur upstream of the probe, and it measures the stagnation pressure and temperature to be 620 kPa and 340 K, respectively. If the static pressure upstream is 110 kPa, determine the flow velocity.
Consider a hypersonic vehicle with a spherical nose flying at Mach 20at a standard altitude of 150,000 ft, where the ambient temperature andpressure are 500◦R and 3.06 lb/ft2, respectively. At the point on thesurface of the nose located 20◦ away from the stagnation point, estimatethe: (a) pressure, (b) temperature, (c) Mach number, and (d) velocity ofthe flow.
Air at 7.20 MPa (abs.) and a temperature 1100K flows isentropically through a converging-diverging nozzle, the throat area is 0.01 m^2. Determine:1- The downstream velocity, in the section where the Mach number is 4.0;2- The mass flow rate through the nozzle
The stagnation pressure after the normal shock wave in a diverging nozzle (pi= 170 kPa, Mi= 2.4, Ax ⁄ Ai = 2.0)
The entropy increase across a normal shock wave is 199.5 J/(kg · K). Whatis the upstream Mach number?
The flow just upstream of a normal shock wave is given by p1 = 1 atm,T1 = 288 K, and M1 = 2.6. Calculate the following properties justdownstream of the shock: p2, T2, ρ2, M2, p0,2, T0,2, and the change inentropy across the shock.
The normal shock wave moves toward the back tank at an underexpansion flow regime during the operation of the converging-diverging nozzle True Or false??
Q1: Air is isentropically expanded from initial values 1500 kPa and 60°C to 400 kPa. What is the ratio of the initial to final speed of sound? R= 0.287 kJ/kg-K and k 1.4
Shock waves are treated as discontinuities here, but theyactually have a very small fi nite thickness. After giving itsome thought, sketch your idea of the distribution of gasvelocity, pressure, temperature, and entropy through theinside of a shock wave.
4. It is important to remember that the isentropic relations and normal shock relationsare monotonic with Mach number and can be inverted. To illustrate this, consider thefollowing problems,(a) Given a total temperature to static temperature ratio of 4, determine the Machnumber.(b) If the entropy rises by ∆s/R = 1.0 across a shock, determine the pre- and post-shock Mach numbers and the static pressure jump (p2/p1).
4. It is important to remember that the isentropic relations and normal shock relationsare monotonic with Mach number and can be inverted. To illustrate this, consider thefollowing problems, (c) If the temperature jumps from 0 Celsius ahead of a shock to 200 Celsius behinda shock, what is the shock Mach number?(d) If the velocity behind a Mach 5 shock wave is 200 m/s, what is the upstreamvelocity?

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