Consider the isentropic flow through a convergent-divergent nozzle with an exit-to-throat area ratio of 2.5. The reservoir pressure and temperature are 1 atm and 288 K, respectively. Calculate the Mach number, pressure, and temperature at both the throat and the exit for the cases where (a) the flow is supersonic at the exit and (b) the flow is subsonic throughout the entire

Q: Carbon dioxide enters an adiabatic nozzle at 1200 K with a velocity of 50 m/s and leaves at 400 K.…

A: (a) Write the values of specific heat and gas constant for carbon dioxide at room temperature from…

Q: A gas is flowing at a supersonic velocity in a gradually increasing cross-sectional area.If the flow…

A: Concept: Given compressible flow,  1.For a gradually increasing cross_sectional area (diffuser) and…

Q: A steady one-dimensional isentropic flow in variable area passages is called “variable area flow”.…

A:

Q: . Air is flowing isentropically through a converging duct which is fed from a large where the…

A: Since you have asked multiple questions in a single request, we would be answering only the first…

Q: Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1…

A:

Q: 3- Mach number at a certain section in a diverging part of a c-d nozzle is 0.7. At farther section…

A: Given dataMach number at a certain section of a c-d nozzle = 0.7Mach number at exit Mexit = 0.4To…

Q: Air flows from a large tank where the pressure and temperature are 600 kPa and 800 K, respectively,…

A: P1=600 KpaT1=800KA2=.0005 m2P2= 100 Kpa T2T1=P2P1γ-1γT2800=1006001.4-11.4T2=479.4695 K

Q: 1. Air is flowing isentropically through a converging duct which is fed from a large temperature and…

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Q: Ahead of the normal shock wave, the upstream pressure , temperature, and Mach number are 0.53 atm,…

A:

Q: A converging–diverging nozzle receives air from a tank at 100 psia and 600°R. The pressure is 28.0…

A: Dear student as per the policy i have solved first three subparts for you please post the…

Q: Air at a total pressure and temperature of 8 atm and 450 K enters a frictionless constant…

A: Given data: Total pressure at inlet, P1=8 atm and temperature at inlet, T1=450 K As the flow of air…

Q: Air at 14 psia, 40°F, and a Mach number of 2.0 is forced to turn upward by a ramp that makes an 8°…

A: Consider the following assumption: The flow is steady. The boundary layer on the wedge is very…

Q: Nitrogen enters a duct with varying flow area at 400 K, 100 kPa, and a Mach number of 0.3. Assuming…

A: Given data as per question intitial temperature = 400 k initial pressure = 100 kpa Mach no. = 0.3…

Q: Air enters a converging–diverging nozzle, as shown at 1.0 MPa and 800 K with negligible velocity.…

A: Given data

Q: A gas is flowing at a supersonic velocity in a gradually increasing cross- sectional area. Assuming…

A: To find :- Correct option

Q: 1. Using the Second and Third-Order Approximations, find the pressure acting on the upper and lower…

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Q: Air is driven from a reservoir at 1.3 MPa through a converging-diverging nozzle with a design Mach…

A: As per BARTLEBY rule i answer only first 3 parts (a,b,c),so i hope you understand.

Q: · Air is flowing isentropically through a converging duct which is fed from a large reservoir where…

A: T1=350 K,P1=250 kPaAC=.005 m2 ,P2=150 kPa T2T1=P2P1γ-1γT2350=1502501.4-11.4T2=302.47 KNow for…

Q: 1. Air is flowing isentropically through a converging duct which is fed from a large reservoir where…

A: We are suppose to solve only one question. Please post other question as a separate question.

Q: A long pipe of 0.0254 m diameter has a mean coefficient of friction of 0.003. Air enters the pipe at…

A: This question is solved by the Mach number relation, To1T1=1+γ-12M12 M1 is the enter Mach number, T0…

Q: when aircraft is flying at subsonic velocity, the pressure at its nose i. e. the stagnation point is…

A: Given P(Stagnation)=160kPa T=298 k P(Ambient )=100kPa

Q: Consider the isentropic flow through a convergent-divergent nozzle with an exit-to-throat area ratio…

A: Consider the diagram shown below for the nozzle as shown below. Given data:

Q: An aircraft flies with a Mach number Ma1 = 0.9 at an altitude of 7000 m where the pressure is 41.1…

A: The stagnation properties of the aircraft are found out,…

Q: Air enters a converging–diverging nozzle at 1.2 MPa with a negligible velocity. Approximating the…

A: Given, P0  = 1.2 MPa Ma = 1.8 Flow is isentropic, so k = 1.4

Q: A gas initially at a supersonic velocity enters an adiabatic diverging duct. Discuss how this…

A: Part (a) The relation between change in velocity and the change in the area comprising Mach number…

Q: An ideal gas with k = 1.33is flowing through a nozzle such that the Mach number is 1.6 where the…

A: Given data:

Q: Air flows through a long, isentropic nozzle. The temp. and pressure at the reservoir are 1000 K and…

A: Given that: Nozzle is isentropic i.e. change in entropy is zero. Temperature of air at entrance = T…

Q: Is it possible to accelerate a gas to a supersonic velocity in a converging nozzle? Explain

A: We have a standard equation, dAA=dpρV21-M2 The above equation is both for nozzle and diffuser, For a…

Q: Consider the supersonic flow of air over a two-dimensional wedge with a half angle of 10 degrees at…

A:

Q: D5. A converging-diverging nozzle operates with air and subsonic flow at the inlet and supersonic…

A: Find , M2 , P2 at exit

Q: Nitrogen enters a duct with varying flow area at 400 K, 100 kPa, and a Mach number of 0.5. Assuming…

A: Given data: The temperature at the inlet of the duct, T1 = 400 K. The pressure at the inlet of the…

Q: A flow of air with Mach number M1 = 2, pressure p1 = 0.7 atm, and temperature 630 deg R is turned…

A: The data given is, δ=26.38° M1=2 P1=0.7 atm T1=630°R

Q: Example: Carbon dioxide flows steadily at a mass flow rate of 3 kg/s and pressure of 1400 kPa and…

A:

Q: Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1…

A: Given data: Initial upstream pressure, P1 = 1 atm. From the standard air properties, the specific…

Q: Air is flowing isentropically through a converging duct which is fed from a large reservoir where…

A:

Q: The pressure upstream of a normal shock wave is 1 atm. The pressure and temperature downstream of…

A:

Q: Air Is flowing isentropically through a converging duct wl)lcJ,,is fed from a. large reservoir where…

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

Q: Consider gas flow through a converging nozzle with specified inlet conditions. We know that the…

A: The gas flowing through a converging nozzle with the inlet conditions which are specified can only…

Q: Problem (1) Air flow adiabatically in a constant area duct. At the inlet of the duct, the Mach…

A:

Q: Q.1. Air flow adiabatically in a constant area duct. At the inlet of the duct, the Mach number,…

A: Given Data : At Inlet Mach Number Mi = 0.6 Pressure Pi = 150 KPa Temperature Ti =300 K Duct Length…

Q: Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.6. If the…

A: Given Mach number = 2.6 Pressure of the air = 58 kPa Air temperature = 270 K To find Pressure…

Q: Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1…

A: Data given-  p01 = 1 atm M1 = 2.5  M1 = 4.5

Q: (a) the exit temperature and,

A: P1=380kPaT1=450KV1=55m/sMa2=0.8k=1.4c=1.005kJ/kgKR=0.287 kJ/kgK To-Find:- a Exit temperatureb Rate…

Q: Consider the isentropic flow through a convergent-divergent nozzle with an exit-to-throat area ratio…

A: Given data Convergent - Divergent. exit Throat = 2.5 a)  P = 1 atm     T = 2881 Find: Mach number…

Q: A stationary normal shock occurs in an air stream when the pressure, temperature and Mach number are…

A: Step 1

Entropy

In physics, entropy means the amount of disorder or the degree of randomness associated with a thermodynamic system. The system is not self-organized when the entropy of the system is high. For instance, when a system is at an elevated temperature, its molecules are in random motion, vibrating and colliding with each other. During this scenario, the probability of finding a molecule at a particular place twice, is low. Under this circumstance, the system can be said to be in a high entropy.