A steady one-dimensional isentropic flow in variable area passages is called “variable area flow”. In this case, the heat transfer is negligible and there is no other irreversibility due to fluid friction. The following relation is for steady one-dimensional isentropic compressible flow through a duct; where A is the cross-sectional area of the duct, V is the fluid velocity, and Ma is the Mach number. With relevant sketching, analyze its implication in the design of converging nozzles and diffusers if Ma is greater than 1.

Q: Asap.. An isentropic flow through a convergent-divergent nozzle with an exit-to-throat ratio of…

A: The ratio of exit area to throat area is The flow through the throat is subsonic.The exit pressure…

Q: 4- The inlet conditions to a steam nozzle are 10 bar and 250°C. The exit pressure is 2 bar. Assuming…

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Q: Air enters a nozzle at 200 KPa, 360 K and a velocity of 180 meter per second . Assuming isentropic…

A: Given: T = 360 K V = 180 m/s k = 1.4

Q: Air at 26 psia, 320°F, and Mach number Ma = 0.7 flows through a duct. Calculate the velocity and the…

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Q: name of the equation that describes the relationship between temperature and saturation vapor…

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Q: (a) Write Area-Velocity relation for compressible flows through a supersonic Convergent-Divergent…

A: In order to overcome this issue, we must address each component separately:(a): Relationship between…

Q: (b) The pressure, temperature and Mach number at the entry of a flow passage are 2.45 bar, 26.5° C…

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Q: Consider a compressible airflow through a pipe. If the flow velocity all throughout the tube is…

A: For compressible flow, we have following relation between the velocity, area and mach number.…

Q: Exercise: Air is supplied to a C-D nozzle from a large reservoir where stagnation pressure and…

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Q: Can the Mach number of a fluid be greater than 1 after a normal shock wave? Explain.

A: Normal shock wave: The normal shock waves for supersonic flow are most likely to occurs in the…

Q: Atmospheric air at 20°C enters and fills an insulated tank thatis initially evacuated. Using a…

A: The data given is, Air temperature entering into the tank, Tatm = 20°C = 293 K The tank stated in…

Q: The relations to convert the oblique shock wave to nomal shock wave. - Continuity equation in…

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Q: - For flow of a compressible fluid from a torage tank through a converging-diverging hannel…

A: Given For flow of a compressible fluid from a storage tank through a converging-diverging channel…

Q: Q/An airstream, at a temperature of 238 K, is moving at a speed of 773 m/s when it encounters an…

A: Temperature inlet = 238 K Velocity = 773 m/s Shock angle B1 = 38o

Q: For steady isentropic flow of perfect gas in constant area duct, the change of gas velocity to the…

A: To find the equation for the isentropic process.

Q: At a point in the flow over an F-15 high-performance fighter airplane, the density,temperature and…

A: Please go through the below answer. This is the second time I'm answering this questionExplanation:

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

A: Given data

Q: Example (4-7): Air is supply to pres temperature at 210 kPa and 318 K where velocity is zero. The…

A: Given data,T01=318k=T0P01=210kPa=P0A2A*=0.120.054=2.222

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

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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: onsider an ideal nozzle of a rocket flying at an altitude where the ambient pressure and mperature…

A: 1) to calculate the nozzle supply pressure, throat area and mass flow rate at ambient pressure 2)…

Q: The Mach number of an aircraft that travels with a speed of 260 m/s in air at 25°C while it…

A: Mach number is defined as the ratio of velocity of jet to the velocity of sound in air at given…

Q: Q.2 Air which enters a diverging duct is slowed by a normal shock wave, as shown in figure. The…

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Q: Consider a flow with pressure and temperature at standard conditions, a pitot tube measures 1.546…

A: Solution:

Q: How does the Mach number affect the behavior of compressible flow in a supersonic nozzle?

A: The Mach number is a dimensionless quantity representing the speed of an object moving through a…

Q: Air flowing at 32 kPa, 240 K, and Ma1 = 3.6 is forced to undergo an expansion turn of 15°. Determine…

A: Given, P1 = 32 kPa, T1 = 240 K Ma1 = 3.6 δ= 15° The deflection angle is equal to the wedge…

Q: An aircraft is flying at an altitude of 100ooft and at a certain part of its airframe a dynamic…

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Q: Nitrogen flows from a reservoir in which its velocity is negligible and its temperature is 22°C. The…

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Q: For oblique shock, the downstream * Mach number is always less than unity O may be less or more than…

A: For a given Mach number, M1, and corner angle, θ, the oblique shock angle, β, and the downstream…

Q: At the entry of a diverging section, the temperature of a gas is 27*C, and the Mach number is 1.5.…

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Q: 4 During the Rayleigh process if the flow is supersonic, due to cooling the velocity all the above…

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Q: 6-In isentropic flow with variable area duct the final form of the momentum equation shows positive…

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Q: A supersonic aircraft at an altitude of 3 km at constant velocity of 650 m/s. the aircraft passes…

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Q: Consider a gas with a specific heats ratio of 1.48 at the Mach number of 6.5. Determine the strength…

A: The specific heat ratio is γ=1.48 The Mach number is M=6.5

Q: An aircraft is flying at an altitude of 10000ft and at a certain part of its airframe a dynamic…

A: Write the expression of velocity at an altitude of 10000 ft. v22=gz-Pρ

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: In your own words, write a summary of the differences between incompressible flow, subsonic flow,…

A: Given Incompressible flow Subsonic flow Supersonic flow To find Difference

Q: Air is cooled as it flows through a 30-cm-diameter duct. The inlet conditions are Ma1 = 1.2, T01 =…

A: Given, Ma1 = 1.2, T01 = 350 K, P01 = 240 kPa  Ma2 = 2.0 diameter of duct (d) = 30 cm

Q: 3. Air enters a converging-diverging nozzle at 1.50 MPa and 900 K with a negligible velocity. The…

A: A converging diverging nozzle is a type of nozzle to produces an exhaust thrust with the help of the…

Q: The Fanning equation is essentially the same as the Darcy-Weisbach equation but differs by their…

A: Darcy's-Weisbach equation is an expression used for calculating major head loss due to friction in…

Q: Consider air entering a heated duct at p1 = 1 atm and T1 = 288 K. Ignore the effect of friction.…

A: p1 = 1 atm T1 = 288 K M1 = 2.2   To find: The amount of heat per unit mass,q.

Properties of Pure Substances

A substance with fixed chemical composition throughout is called a pure substance like water, air, and nitrogen. A pure substance does not have to be a single element or compound. A mixture of two or more phases of a pure substance is also a pure substance as long as the chemical composition is the same for all phases. These substances mainly have a constant/ uniform composition. The substances also have fixed boiling and melting points. A pure substance takes part in a chemical reaction to form predictable products.