(b) A normal shock wave passes through stagnant air at 22°C and atmosphericpressure of 130 kPa with a speed of 465 m/s as shown in Figure 3. Assumey= 1.4 and R= 287 J/kg.K.P2V1V2Stationary shock waveFigure 3[Gambarajah 3](i) Determine the pressure and temperature downstream of the normal shockwave.(ii) Determine the velocity in the air immediately behind the normal shockwave.

Answered: Image /qna-images/answer/e0a0101f-ae53-48ab-aa50-40c07fffc8e2.jpg

(b) A normal shock wave passes through stagnant air at 22°C and atmospheric pressure of 130 kPa with a speed of 465 m/s as shown in Figure 3. Assume y= 1.4 and R= 287 J/kg.K. P, P2 V1 V2 Stationary shock wave

(b) A normal shock wave passes through stagnant air at 22°C and atmospheric pressure of 130 kPa with a speed of 465 m/s as shown in Figure 3. Assume y= 1.4 and R= 287 J/kg.K. P, P2 V1 V2 Stationary shock wave

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

See similar textbooks

Related questions

Q: 5. The upstream Mach number for a given Prandtl-Meyer expansion is 3.2 and the pressure ratio…

A: When an amount of force act on the surface of the object in perpendicular direction what has the…

Q: Supersonic air at Ma1 = 2.0 and 230 kPa flows parallel to a flat wall that suddenly expands by ? =…

A: Assumption The flow is steady The boundary layer on the wall is very thin Properties: The fluid…

Q: Downstream of a normal shock wave, in airflow, the conditionsare T2 = 603 K, V2= 222 m/s, and p2 =…

A: Given that, Mach Number at state 2 will be calculated as follows,

Q: The velocity and temperature behind a normal shock wave are 329 m/s and 1500 K, respectively.…

A: Step-1 The velocity of the normal shock wave is: v2 = 329 m/s The temperature of the normal shock…

Q: Supersonic flow passes along the -6 wing shown in figure. There are Two oblique shock waves and two…

A: Solution (6): The wave of strong pressure caused by extreme pressure change by the explosions,…

Q: 1- to convert the moving nomal shock wave to stationary normal shock wave

A: Conversion from moving shock wave to stationary shock wave is presented. Subsequently, governing…

Q: An explosion in air, k = 1.4, creates a spherical shock wave propagating radially into still air at…

A: (a) Calculate the Mach number. p2p1=1+2γγ+1M2-11400101.3=1+21.41.4+1M2-1M=3.4625

Q: Consider the Gulfstream IV flying at Mach = 0.35. Calculate thrust required given an altitude of…

Q: A supersonic inlet is sketched below and contains an oblique shock wave followed by a normal shock…

A: Given:M1=3T1=300 KP1=101.3 KPa

Q: Q2/ Answer the following: 1) Separation in flow past a solid object is caused by (a) a favourable…

A: 1. Seperation in flow past a solid object is caused by an adverse (posituve) pressure gradient. 3.…

Q: Consider an oblique shock wave with a wave angle equal to 35 degree. Upstream of the…

A: Stagnation point: The point at which the velocity of the fluid becomes zero. When the fluid is…

Q: 1- Calculate the pressure, temperature and velocity prior to the shock wave. 2- Determine if the…

Q: A piston moves along a tube containing air at an initial sound speed of 330 m/s. When the piston…

Q: A supersonic aircraft flies with a speed of 2750 km/h at 27 °C and 100 kPa weather conditions. Two…

A: Note :- you have posted multiple questions on single window. As per the guidelines I am able to…

Q: Consider a normal shockwave in air where the upstream flowproperties are u1 = 680 m/s, T1 = 288 K,…

A: Given data: The upstream velocity is, U1 = 680 m/s. The upstream temperature is, T1 = 288 K. The…

Q: Air at 1 MPa and 600 °C enters the convergent Lule shown in Figure 2 at a speed of 150 m/s.Mass flow…

Q: Consider a normal shock wave in air The upstream conditions are given by M = 3; 1 atm, and p1 M2,…

A: From the given data: p1=1 atm = 101.32 kPaInitial temperature is given…

Q: c) Prove mathematically that shock wave cannot occur in subsonic flow

A: Solution: Change in entropy across shock is given by, ∆sR=γγ-1ln2(γ+1)M2+γ-1γ+1+1γ-1ln2γγ+1M2-γ-1γ+1…

Q: In an undisturbed airstream, where the pressure is 14.7 10/in^2 and the temperature is 519 degrees…

Q: a) Derive an expression for a relation between pressure and area changes in one- dimensional, steady…

A: a) Since, h0=h+V22differentiating we get0=dh+VdVdh=-VdV.....equation 1 From property relation,…

Q: Calculate the change in Temperature (T2) after a cooled Helium gas with velocity (v1) and speed of…

A: Given data Speed of Helium = v1 = 642.78 m/sSpeed of sound = va1 = 360.51 m/s

Q: An air stream, with T1 =0 C, p1 = 60.0 kPa (abs), and V 497 m/sec, undergoes a normal shock.…

Q: A Rayleigh flow at Mach = 0.3, P1 = 150KPa and T1 = 80oC, enters a non-adiabatic pipeline. It adds…

Q: The pressure ratio across a normal shock wave is given by the following equation: P2 P1 P2 P1 Show…

A: The given relation to be proven is : P2P1 = γ+1γ-1ρ2ρ1-1γ+1γ-1 - ρ2ρ1

Q: diheoat = 8 cm 1 2 Exit Po da = 18 cm Shock wave Figure 4 [Gambarajah 4] (i) Determine the Mach…

A: The nozzle is a device that has varying cross-sections, in which pressure is reduced by expansion…

Q: (7) The entropy change across a normal shock wave (Tox= 505 K, vx= 490 ms-1), * O 0.0008 Jkg-1K-1…

A: Given:Tox=505 KVx=490 m/s

Q: Consider a diamond-wedge airfoil such as shown , with ahalf-angle ε = 10◦. The airfoil is at an…

Q: Air flows through a duct as in Fig, where A1 =24 cm2, A2 = 18 cm2, and A3 = 32 cm2. A normalshock…

A: Given: Mach number at section 1,Ma1=2.5 The pressure at section 1,p1=40 kPa The temperature at…

Q: Po70 kPa T300 K Va Soo ms flow direction "Normal shock wave

Q: 3.4. Consider a normal shock wave in air The upstream conditions are given by M = 3; P1 = 1 atm, and…

A: Since you have posted a question with multiple subparts, we will solve the first three subparts for…

Q: The convergent-divergent nozzle in Figure 22 expands and accelerates dry air to supersonic speeds at…

Q: The flow just upstream of a normal shock wave is given by p1 = 1 atm,T1 = 288 K, and M1 = 2.6.…

A: Given: properties at upstream of a normal shock p1=1 atmT1=288 kM1=2.6 To find The properties just…

Q: Q2) Uniform airflow at Mach 3 passes into a concave corner of angle 15°, as shown in Figure. The…

A: Write the expression of the relation between θ-β-M.

Q: Consider a supersonic flow with M = 2, p = 1 atm, and T = 288 K. This flow isdeflected at a…

A: The Mach number of the flow M=2 The pressure of the flow p=1 atm The temperature of the flow T=288 K…

Q: Consider a normal shock wave at sea level with the density ratio, p2/p1 = 2.67. What are the…

A: A normal shock occurs when the shock wave is perpendicular to the flow direction. If the flow is…

Q: Consider a low-speed subsonic wind tunnel designed with a reservoir cross-sectional area A, = 2 m2…

A: Reservoir area (A1)= 2 m2 Test -section cross sectional area (A2)= 0.5 m2 pressure( P2) = 1 atm =…

Q: 1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle…

Q: The Mach number behind a normal shock wave is 0.4752. What is the Mach number in front of the wave?…

A: the Mach number in front of the wave…

Q: When an oblique shock strikes a solid wall, it reflects as ashock of sufficient strength to cause…

A: Given, Ma1 = 2.5 β1 = 40o p1 = 100 kPa

Q: 3.4. Consider a normal shock wave in air The upstream conditions are given by M = 3; 1 23 kg/m'…

A: Data given- M1 = 3 P1 = 1 atm ρ = 1.23 kg/m3 Need to calculate the downstream values

Q: When a sea-level flow approaches a ramp of angle 20°, anoblique shock wave forms as in Figure .…

A: Given Ramp angle = 20o To find (a) Ma1 (b) p2 (c) T2 (d ) V2

Q: Q1) Air at mach number 2 over a wedge and generation of an oblique shock wave 40° . determine : 1.…

Q: Show that for isentropic flow of a perfect gas if a pitot- static probe measures Po, p, and Tg, the…

A: Given: Isentropic flow of a perfect gas

Q: A large reservoir at 20 °C and 800 kPa is used to fill a smallinsulated tank through a…

A: Given: throat area = 1 cm2 exit area = 1.66 cm2 volume= 1 m3 To determine: (a) Elapsed time when…

Q: Air at Ma1 = 2.0 and p1 = 100 kPa undergoes an isentropicexpansion to a downstream pressure of 50…

A: GivenMach no. before the turn, Ma1=2 Pressure before the turn, p1=100 kPa Pressure before the turn,…

Question

(b) A normal shock wave passes through stagnant air at 22°C and atmospheric
pressure of 130 kPa with a speed of 465 m/s as shown in Figure 3. Assume
y= 1.4 and R= 287 J/kg.K.
P2
V1
V2
Stationary shock wave
Figure 3
[Gambarajah 3]
(i) Determine the pressure and temperature downstream of the normal shock
wave.
(ii) Determine the velocity in the air immediately behind the normal shock
wave.

Expert Solution

This question has been solved!

Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.

This is a popular solution!

SEE SOLUTION Check out a sample Q&A here

Step 1

VIEW

Step 2

VIEW

Step 3

VIEW

Trending now

This is a popular solution!

Step by step

Solved in 3 steps with 3 images

SEE SOLUTION Check out a sample Q&A here

Knowledge Booster

Learn more about

Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.

Similar questions

are 3000 ft/s and 500°R, respectively Calculate the Mach number M and the characteristic Mach number M* at this point 3.4. Consider a normal shock wave in air The upstream conditions are given by M = 3; P1 M2, u2, Po,, and T %3! = 1 atm, and p, = 1 23 kg/m Calculate the downstream values of P2, 02 35 Consider a Pitot static tube mounted on the pose of an experımental airplane A
Show that for isentropic flow of a perfect gas if a pitot- static probe measures Po, p, and Tg, the gas velocity can be calculated from (k-1Vk v - 2,7, 1 - What would be a source of error if a shock wave were formed in front of the probe?
Activity No. 1 Title: Pressure, Density, Temperature, and Mach Number Changes Across a Normal Shock Wave Explanation of Table Column No.: 1, M₁ given S (2), P7M₁-1 R 6 6M,² M₂² +5 (7M,'-1XM, +5) 36M, M₁² +5 7M-1 P₂ P T. T₁ 5 M₂
This year's qualification round featured a spaceship escaping from a shock wave (Problem B). The crew survived and wants to study the shock wave in more detail. It can be assumed that the shock wave travels through a stationary flow of an ideal polytropic gas which is adiabatic on both sides of the shock. Properties in front and behind a shock are related through the three Rankine-Hugoniot jump conditions (mass, momentum, energy conservation): Pivi = P2V2 Pivi + P1 = p2u3 +p2 + h2 + hị = 2 where p, v, p, and h are the density, shock velocity, pressure, and specific enthalpy in front (). and behind (2) the shock respectively. Shock front v2, P2; P2, h2 V1, P1, P1, h1 (a) Explain briefly the following terms used in the text above: (i) stationary flow (ii) polytropic gas (iii) specific enthalpy (b) Show with the Rankine-Hugoniot conditions that the change in specific enthalpy is given by: P2 - Pi 1 Ah = 2 P1 P2 The general form of Bernoulli's law is fulfilled on both sides of the shock…
3.4. Consider a normal shock wave in air The upstream conditions are given by M1 = 3; 1 23 kg/m' Calculate the downstream values of p2, T,, 1 atm, and p1 M2, u2, Po,, and T, P1 P24 02 Dis
Q2: Air (y = 1.4) enters a converging-diverging diffuser with a Mach number of 2.8, static pressure pi of 100 kPa, and a static temperature of 20°C. For the flow situation shown in Figure, find the exit velocity, exit static pressure, and exit stagnation pressure. Ans: Ve = 55.093 m/s; Pe = 2236.678 kPa; Poe = 2252.44 kPa i M₁ = 2.8 A₁ = 0.10 m² A₂ = 0.50 m² A₁ = 0.25 m²
4. What is the limit of density change across a Normal shock wave in perfect gas. P2_ Y +1 lim M1-00 PI Y - 1
(7) The entropy change across a normal shock wave (Tox= 505 K, vx= 490 ms-1), * O 0.0008 Jkg-1K-1 O 0.23 Jkg-1K-1 O 0.01171 Jkg-1K-1 O 3.36 Jkg-1K-1
Consider a normal shock wave at sea level with the density ratio, p2/p1 = 2.67. What %3D are the pressure, density, temperature, velocity and Mach number downstream of the wave?
Z\0 @ P 0:10 ZAIN IQ II. Quiz 2 Thermo.pdf Gas flowing through a diverging nozzle has at inlet section a temperature of 20 °C, pressure 120 kN/m² and velocity 300 m/s. At the outlet of the nozzle the velocity has fallen to 100 m/s. Assuming an adiabatic flow, what is the values of outlet pressure, temperature, internal energy and specific enthalpy at outlet section. Take y= 1.333 and Cv= 0.86 kJ/kg K.
Q6: Air following through constant area duct encounters stationary shock as shown in figure. Find the Mach number, temperature, pressure, stagnation pressure, stagnation temperature and velocity after the shock. Ans.: M2 = 0.6746, T2 = 344 K, p2 = 137 kPa, To = 375 K, po = 186 kPa. V1=500 m/s P;=50 kPa 1-250 K → (1) | (2)
A normal shock occurs in a stream of oxygen. The oxygen flows at Ma=1.8 and the upstream pressure and temperature are 40 psia and 85 degrees Fahrenheit. a) Calculate the following on the downstream side of the shock: static pressure, stagnation pressure, static temperature, stagnation temperature, static density, and velocity. b)If the Mach number is doubled to 3.6, what will be the resulting values of the parameters listed in part (a)?