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. section 1. diverging X 2. converging X3. entry X 4. throat

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. section 1. diverging X 2. converging X3. entry X 4. throat

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: the flow phenomenon across a convergent and divergent nozzle when the p the stagnation pressure at…

A: Function of Nozzle A nozzle is a fluid-accelerating device. The velocity of the fluid increases as…

Q: 48. Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. 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: Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The…

Q: 2019 \ 2020 static pressure in the air stream is 50kpa, static temperature is 298K. Calculate Answer…

A: Mach no is a property of the fluid that represents the ratio of flow velocity across a boundary to…

Q: Consider an oblique shock wave with a wave angle of 30◦ in a Mach 4flow. The upstream pressure and…

Q: 16. Air is expanded through a convergent-divergent nozzle from a large chamber in which the pressure…

Q: A fuel–air mixture, assumed equivalent to air, enters a ductcombustion chamber at V1 = 104 m/s and…

A: Given: The initial temperature,T1 300 K The initial velocity, V1=1.4 m/s Solution:

Q: 02: The large compressed-air tank shown in the figure bellow exhausts from a nozzle at an exit…

Q: A subsonic inlet diffuser of area ratio 3 is employed in a Mach-2 jet engine. A normal shock is…

A: Normal shock at inlet and in downstream region isentropic relations are used to arrive the solution.

Q: Q2: Air at a stagnation temperature 365K and a stagnation pressure 760 kpa flows through a…

A: Given data as per question Stagnation temperature =365 k stagnation pressure =760 kpa Back pressure…

Q: 45. 4.7. The temperature of argon is 100 F, the pressure 42 psia, and the velocity 2264 ft/ sec.…

Q: Uniform air flow at Mach 3 passes into a concave corner of angle 15°, as shown in Figure P6.1. The…

Q: Question 3 ULO2 A Laval nozzle has a Mach number of 0.4 (located near the inlet at section 1) where…

Q: Q2: The large compressed-air tank shown in the figure bellow exhausts from a nozzle at an exit…

A: Given Data exit velocity, Ve=235 m/s k=1.396 Cp=917 J/kg·K R=260 J/kg·K T=30 oC =30+273=303 K (a)…

Q: An airflow at Mach 0.6 passes through a channel with a cross-sectional area of 50 cm?. The static…

A: Please find the solution below

Q: 6.9 A convergent-divergent nozzle is fixed on the side of a vessel containing air at 10 bar abs and…

A: Given: Stagnation pressure = 10 bar Stagnation temperature = 80+273 =353 K exit pressure = 1 bar

Q: Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The…

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

Q: Q1/ An aircraft has a turbojet engine and a convergent nozzle. Where the inlet section parameters…

A: Convergent nozzle increases the flow speed by restricting the flow path. For high nozzle pressure,…

Q: Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The…

Q: A convergent-divergent nozzle with an exit-to-throat area ratio of 1.616has exit and reservoir…

A: The given pressures are: The pressure ratio is The Mach number and the area ratio at the exit with…

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: 13.8 (a) Describe briefly the various losses occurring in an inward- flow radial turbine stage. (b)…

A: The radial flow turbine is defined as the turbine in which flow enters radially. The main difference…

Q: Q2: The large compressed-air tank shown in the figure bellow exhausts from a nozzle at an exit…

Q: A supersonic nozzle is used for discharging air from a reservoir. The reservoir pressure and…

A: normal shock and isentropic relations are used to arrive the solution.

Q: When the Apollo command module returned to earth from the moon, itentered the earth’s atmosphere at…

A: Given data The mach number is M=36 The free-stream temperature is T∞=300 K The ratio of specific…

Q: Question one Air flow at Ma 2.2 takes a compression turn of 12° and then %3D another turn of angle 0…

Q: Fuel is to be burned in a stream of air moving with a Mach No. 2.0, a temperature (-160 F), and a…

Q: Q1: Air enters a converging-diverging nozzle having throat diameter of 8.5cm and exit diameter 28cm.…

A: Given, Throat diameter, dT=8.5cm=0.085 m Exit diameter, dE=28cm=0.28m The cross-sectional area of…

Q: Air, with stagnation conditions of 800 kPa and 100°C, ex pands isentropically to a section of a duct…

Q: When a pitot tube such as in Fig. is placed in asupersonic flow, a normal shock will stand in front…

A: Given data: The Mach number inside the shock can be determined as,

Q: Air is flowing in a convergent nozzle. The stagnation pressure is 350 KPa , the stagnation…

Q: Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The…

A: A spout is a somewhat straightforward gadget, simply an exceptionally formed tube through which hot…

Q: (a) A pitot tube indicates a pressure of 265 kPa in an airstream in which the temperature is 10°C…

A: Given that, Po=265 kPa,To=10 °C=283 K,Mach number, M=1.5, The pressure ratio is given as,…

Q: Air flows isentropically in a converging-divergingnozzle with a throat area of 3 cm2. At section 1,…

A: Given: Throat area A=3 cm2P1=101 kPaT1=300 KV1=868 m/s To determine: Whether the flow is choked or…

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

Q: At the point where the air enters the convergent nozzle, its static pressure is 150 kPa, its…

A: Nozzle: Nozzle is a device that is mostly used for creating high velocity jets. It has varying cross…

Q: 21: Air enters a converging-diverging nozzle having throat diameter of 8.5cm and exit dian 8cm. the…

A: Nozzle is a device that is varying in cross section, in which pressure is reduced by expansion.…

Q: Consider steady, isentropic flow of air through a duct with varying area. At section 1, p1 = 60.0…

Q: The throat and exit areas of a convergent divergent nozzle in a wind tunnel are 4 cm2 and 10 cm?…

Q: 3. Assume a supersonic flow with M=2, P=1 atm, and T=288 K that is deflected via 15° at a…

A: Given data Mach Number M1=2 Pressure P1=1 atm Temperature T1=288K Deflection angle θ=15o To…

Q: Assume that a supersonic converging-diverging nozzle operating isentropically delivers air to a…

Q: In the test section of a supersonic wind tunnel, a Pitot tube in the flowreads a pressure of 1.13…

A: Given, Stagnation pressure p02 = 1.13 atm Static pressure p1 = 0.1 atm

Q: 94. 6.16. Nitrogen flows through a converging-diverging nozzle designed to operate at a Mach number…

Q: The stagnation pressure and temperature at the entry of a nozzle are 5 bar and 500 K respectively.…

A: Introduction: Flow rates are affected by feed pressure and the viscosity of the sprayed liquid.…

Question

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

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 3

VIEW

Step by step

Solved in 3 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

Air flows from a tank through a nozzle into the standardatmosphere, as in Fig. A normal shock stands in theexit of the nozzle, as shown. Estimate (a) the pressure inthe tank and (b) the mass flow.
The converging–diverging nozzle shown in Fig. P3.22expands and accelerates dry air to supersonic speeds at theexit, where p 2 = 8 kPa and T 2 = 240 K. At the throat, p 1=284 kPa, T 1 = 665 K, and V 1 = 517 m/s. For steadycompressible fl ow of an ideal gas, estimate ( a ) the mass fl owin kg/h, ( b ) the velocity V 2 , and ( c ) the Mach number Ma 2 .
1. Air, with stagnation conditions of 800 kPa and 100 °C, ex pands isentropically to a section of a duct where A₁ = 20 cm² and p₁ = 47 kPa. Compute ( a ) Ma₁ , ( b ) the throat area , and ( c ) m . At section 2 between the throat and section 1, the area is 9 cm². (d) Estimate the Mach number at sec tion 2. Plz sketch and solve it
Air flows through a duct as in Fig, where A1 =24 cm2, A2 = 18 cm2, and A3 = 32 cm2. A normalshock stands at section 2. Compute (a) the mass flow,(b) the Mach number, and (c) the stagnation pressure atsection 3.
In Fig. water exits from a nozzle into atmosphericpressure of 101 kPa. If the fl ow rate is 160 gal/min and frictionis neglected, what is the gage pressure at section 1?( a ) 1.4 kPa, ( b ) 32 kPa, ( c ) 43 kPa, ( d ) 29 kPa, ( e ) 123 kPa
The upstream flow properties are T1= 280 K and V= 2000 mph. What is downstream Mach number?
Air flows isentropically in a channel. Properties at section1 are V1 = 250 m/s, T1 = 330 K, and p1 = 80 kPa. Atsection 2 downstream, the temperature has dropped to 0°C.Find (a) the pressure, (b) velocity, and (c) Mach number atsection 2.
A uniform supersonic flow of air at Mach 3.8, with a stagnation pressure of 5.0 MPa and stagnationtemperature of 1100 K, expands around a 23o convex corner. Determine the downstream Mach
Suppose a gas flows through a constant insulated path. Parameters of temperature, pressure and mach is 520R, 50psi and 0.45 respectively. A point in the downstream calculated the mach number to equal to 1. Calculate for the temperature and pressure downstream. Methane Gas (k=1.32, R=96.4 ft-lbf/ lbm-R) 1 slug = 32.174 lbm
Consider the Gulfstream IV flying at Mach = 0.35. Calculate thrust required given an altitude of 30,000-ft, assuming weight of 73,000-lb. Airplane data: S = 950 ft2, AR = 5.92, ??? = 0.015, and K = 0.08 a. The thrust required at 30,000-ft. (in pounds)
Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The throat area is one-half that of the discharge of the divergent section. Assuming the Mach number in the throat is 0.75, what are the values of the following quantities at the throat: pressure(atm), temperature(K), linear velocity(m/s), density(kg/m3), and mass velocity(kg/m2s)? Write your answers according to order of properties asked.
Air, at stagnation conditions of 500 K and 200 kPa, flows through a nozzle. At section 1, where the area is 12 cm², the density is 0.32 kg/m³. Assuming isentropic flow, (a) find the mass flow. (b) Is the flow choked? If so, estimate A*. Also estimate (c) p₁ and (d) Ma₁.