Answered: (4) The back pressure such that there…

(4) The back pressure such that there is a normal shock wave stands at exit plane, (pox = 240 kPa, area ratio = 2.5), * 103.7 kPa 384.4 kPa 124.6 kPa 462.2 kPa

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: A constant area adiabatic wind tunnel is to be designed to provide a test section of air flowing at…

A: Given Data The mach number is: M=3 The pressure is: 7 kPa The temperature is: 255 K The stagnation…

Q: Q3) A convergent-divergent nozzle has a cross-sectional area at the throat of 0.1 m² Air enters the…

Q: The velocity of flow after a normal shock wave when (Tx= ,315 K, vx= 555 ms-1) 275.7 ms-1 O 396.1…

Q: me nole Air flows from a reservoir maintained at 25 °C and 5 bar. It flows through a nozzle Pe:?…

A: Given Data The inlet temperature of the air is: T1=25°C The inlet pressure is: P1=5 bar The throat…

Q: a converging-diverging

Q: H2O gas enters a convergent-divergent nozzle, with pressure 5 MPa, and temperature 2000∘ C. Flow…

A: Given: To = 2000+273 = 2273 K Po = 5 MPa Correct option: 1100 m/s

Q: What would you have to do to reduce this flow angle to zero degrees?

A: Here the reducing flow by zero degree angle attack

Q: Q3) A convergent-divergent nozzle has a cross-sectional area at the throat of 0.1 m² Air enters the…

Q: Q.5. With careful design, one can orient the bend on the lower wall so that the reflected wave is…

A: Please find the solution below

Q: Q2: Helium in a isentropically process. What are the lowest temperature and pressure that can be…

Q: The stagnation density after the shock (px= 55 kPa, Tx= 335 K, vx= 525 ms- ‚1) 0.26 kgm-3 O 0.77…

Q: The velocity of flow after a normal shock wave when (Tx= 315 K, vx= 555 ,ms-1) 275.7 ms-1 O 282.6…

A: Given: Temperature (T) = 315 K Velocity (Vx) = 555 m/s To find: Velocity after shock

Q: : Air flows from a reservoir maintained at 25 °C and 5 bar. It flows through a vith throat and exit…

A: Given:temperature, T=25o Creservoir pressure, P1=5 barthroat diameter, dt=5 cmexit diameter, de=10…

Q: Nozzle is assuming steady one-dimensional flow. M = 2.731. This is the the supersonic flow of air…

A: To calculate the mass flow rate of air through the nozzle, we can use the continuity equation, which…

Q: An air formed a shockwave with a Mach of 2.3. What is the pressure downstream when the pressure…

A: Write the expression for the static pressure before the normal shock. Here, ρ represents the…

Q: 31. Find the altitude of a supersonic airplane (T = - 52 C°, v = 730 m-s) when the time between…

Q: The stagnation pressure after the normal shock wave in a diverging nozzle (pi= 170 kPa, Mi= 2.4, Ax…

A: given; pressure(Pi)=170KPamack number(M)=2.4stagnation pressure(Po)=?specific heat ratio of air…

Q: If 쏘= 1.296, P2 = 387kPa. The static exit pressure P2 equal to %3D %3D A. a. P2 = 510 kPa %3D Shock…

Q: propagates at à speed of normal shock wa m/s down a pipe thát is filled with hydrogen. The hydrogen…

Q: Air flows through a normal shock wave, upstream conditions are V₁= 650 m To1= 550 k and po₁= 750…

A: First of all what is stagnation properties? The isentropic stagnation state is defined as the state…

Q: Q2/ Air flows isentropically in a converging-diverging nozzle with initial Ma = 0.2, pressure = 1…

Q: H2O gas enters a convergent-divergent nozzle, with pressure 5 MPa, and temperature 2000∘ C. Flow…

A: Givenstagnation temperature = 2000 deg C stagnation pressure = 5 MPa exit temperature = 909 K

Q: Q4: : The pressure ratio across a normal shock wave that occurs in air is 1.4. A head of the shock…

Q: The stagnation pressure across ,a normal shock wave is always poy ≥ pox O poy = pox O poy pox O

A: Option: is correct poy < pox Because across the normal shock wave the stagnation pressure…

Q: The stagnation density after the shock (px= 55 kPa, Tx= 335 K, vx= 525 ms-1),

Q: Compressible pipe flow with heat addition, , assumesconstant momentum (p + ρV2) and constant mass…

A: Given: Rayleigh flow: Compressible pipe flow with heat addition, , assumes constant momentum (p +…

Q: Determine the location of a stationary normal shockwave in a C-D nozzle. The back-pressure to…

A: Step 1: Understanding the problemThe problem asks us to determine the location of a stationary…

Q: Q2. Correct the false statement. 1) An oblique shock wave is always parallel to the incoming flow.…

A: 1. An oblique shock wave is inclined with respect to incident upstream flow direction.

Q: Q3: Supersonic divergent duct with Mach inlet 3 and exit Mach number equal to 0.4. Normal shock wave…

A: Given, Inlet Mach number, M1=3AiAi*=4.2346Outlet Mach number,M2=0.4AeAe*=1.5901AlsoAiAe=0.5 (Given…

Q: Q6:An air nozzle has an exit areal.8 times the throat area. If a normal shock occurs at a plane…

A: Given, Po=760KPa,To=350KAeAt=1.8AxAt=1.3considering specific heat ratio, y=1.4 Now, From gas…

Q: H2O gas enters a convergent-divergent nozzle, with pressure 5 MPa, and temperature 2000∘ C. Flow…

A: Given: Let us consider the given, Stagnant Temperature, T0=2000°C+273=2273 k Exit temperature,…

Q: The stagnation pressure after the normal shock wave in a diverging nozzle (pi= 170 kPa, ,Mi= 2.4,…

Q: Problem 4. A converging-diverging nozzle, a with throat area of A = 10 cm?, is attached to a large…

A: Data given - At= 10cm2 Ae = 14 cm2 Po = 8 bar = 8×105 Pa To= 350 K r= 1.4

Q: Q2: Air flows isentropically through converging nozzle which has a throat of 7 cm?. The stagnation…

A: Given data: - The throat area of the nozzle is A = 7 cm2. The stagnation pressure is Po = 130 kPa.…

Q: Sea-level standard air is sucked into a vacuum tank through a nozzle, as in Fig. P9.63. A normal…

A: Given:The area at the throat is the nozzle area is the area at point 4 is

Q: 02: Air flows isentropically through converging nozzle which has a throat of 7 cm?. The stagnation…

Q: Can you do part c please

A: fig: CD nozzle At=.1 m2A1=.1775m2P0=101 kPaT0=15oC=288 K A1=A2 A1A*=.1775.1=1.775 From isentropic…

Question

(4) The back pressure such that there is a normal shock wave
stands at exit plane, (pox = 240 kPa, area ratio = 2.5), *
103.7 kPa
384.4 kPa
124.6 kPa
O 462.2 kPa

Expert Solution

This question has been solved!

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

SEE SOLUTION Check out a sample Q&A here

Step 1

VIEW

Step 2

VIEW

Step by step

Solved in 2 steps

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

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?
section If the back pressure is low enough and the throat is sonic, the Mach number is more than I in a/an during flow in a convergent-divergent nozzle. 1. diverging X2. converging X 3. entry X 4. throat
Q1. A turbojet aircraft flying at speed of 1645 km/h and altitude of 9000 m. A supersonic intake was designed with a conical center body, which generated one oblique shock wave and normal shock wave at the inlet of the aircraft. The deflection of the conical center body is a 10°. Calculate the fluid flow properties and velocity at the aircraft inlet of the intake. Assume a weak solution. Take: R= 0.287 kJ/kg K, and Cp=0.9 kJ/kg K.
غفران عطيه لفتة A supersonic airplane flies at two altitudes, find the temperature of air at second level, (v2 = 755 m-s, u1 = 28°, the Mach no. ratio is 1.1). %3D
Upstream of the throat of an isentropic converging-diverging nozzle at section (1), V₁ = 150 m/s, P1 = 100 kPa (abs), T₁ = 20°C. If the discharge flow is supersonic and the throat area is 0.10 m², determine the mass flowrate in kg/s for the flow of air. kg/s m = i
A turbine nozzle vane at high speed exhibits a normal shock. The flow is modelled as analogous to that through a convergent-divergent de Laval nozzle with a normal shock at the nozzle exit. Just upstream of the shock, the exit Mach number Me = 1.09, the absolute static pressure pe = 280 kPa, the static temperature Te = 586 K, the ratio of specific heats of the combustion productsk = 1.35, and the constant pressure specific heat capacity Cp = 1027 J-kg "K-1. Assuming the combustion products are constant property ideal gasses, determine the density of the combustion products pp after the shock. State your answer in kg m to two decimal places and enter the numerical value only.
A gas which has a molar mass of 39.9 and a specific heat ratio of 1.67 is dis- charged through a nozzle. A normal shock wave occurs at a section of the flow at which the Mach number is 2.5, the pressure is 40 kPa and the temperature is -20°C. Find the Mach number, pressure, and temperature downstream (i.e., after) this normal shock wave. Solution FIGURE E5.2 Shock wave M₁ =25 P₁ = 40 kPa T₁ = 253 K
(6) The coefficient of discharge 1 point for a real nozzle (Theoretical mass flux= 639.8 kgs-1m-2, To= 510 K, Theoretical exit pressure= 67 kPa, Actual exit Mach no. =2.02) * 0.88 0.89 0.90 0.92
i need the answer quickly
A radial flow reaction turbine has the following characteristics: Circumferential area at entrance and exit: Ag = 258 cm² ,Ac2 = 180 cm² ; Q = 0.1n7 = 0.82 ,r, = 25 cm, r3 - 12.5 cm, B, = 140°, Bz = 155°, az = 90°, 0, = 0.75, and nwyd = 92 % . Assume shockless entrance of water to blade. Find: (a) The rotative speed under these conditions, in rpm (b) The hydraulic Torque, in k) The Brake Power in kW (c) (d) the coefficient of velocity c, at entrance to blade (e) The net Head, in m. (f) Draw the velocity diagram and label.
3. Assume a supersonic flow with M=2, P=1 atm, and T=288 K that is deflected via 15° at a compression corner. Determine M, P, T, as well as PO and TO behind the associated oblique shock wave.
(5) (a) Air flows adiabatically through a duct. At point 1 the velocity is 240 m/s, with T₁ = 300 K and P=150 kPa. Compute (a) To1, (b) Po1, (c) Po1, (d) Mal, (e) Vmax, and (f) V*.