An ideal isentropic nozzle is attached to an infinite reservoir that has stagnation conditions 3 MPa and 2250 K, and a constant specific heat of 1.2. If the nozzle's static exit pressure is 38.871 kPa, what is the exit static temperature? Also determine the nozzle's exit Mach number, stagnation pressure, and stagnation temperature.

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: The shock wave photograph of a wedge structure is given. By using this photograph determine the Mach…

A: Given Wedge To find The Mach number from the photograph

Q: Q.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C…

A:

Q: We are given the pressure on one side of a normal shock wave is 1 atmosphere, and the pressure and…

A: given Px = 1atm Py = 10 atm , Ty = 775K

Q: Can a turbine rotation really reach supersonic speed? What is the usual cut-out speed for wind…

A: Question 1 solution:-  ( i ) The turbine pieces are spinning quite fast, thus its blade tips may be…

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

A: In the case of gas with supersonic velocity passing through a converging duct (adiabatic), there is…

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: Can a shock wave develop in the converging section of a converging–diverging nozzle? Explain.

A: In order to produce a shock wave, the flow must be a supersonic flow. Supersonic flow: The velocity…

Q: What is the effect of heating the fluid on the flow velocity in subsonic Rayleigh flow? Answer the…

A: Rayleigh flow is defined as a non-adiabatic, frictionless flow which passes through a fixed area…

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: A supersonic fixed-geometry inlet is operating at sea level where the temperature and pressure are…

A:

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: Air flowing at 8 psia, 480 R, and Ma1 = 2.0 is forced to undergo a compression turn of 15°.…

A: From Prandtl-Meyer function relation,…

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: Compressed air from the compressor of a gas turbine enters the combustion chamber at T1 = 700 K, P1…

A: Given,  T1 = 700 K P1 = 600 kPa Ma1 = 0.2. Mach number is less than 1. So the flow is subsonic.…

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: vortex generators on the upper surface of a wing will

A: Vortex generators on multiengine aircraft increase controllability at low airspeeds and reduce…

Q: 8. Air is flowing through a wide channel at a Mach number of 2 at a pressure of 140 kPa. The upper…

A:

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: A centrifugal compressor has an impeller tip speed of 360 m/s. Determine the absolute Mach number of…

A:

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

A:

Q: What would happen if we tried to further accelerate a supersonic fluid with a diverging diffuser?

A: When the supersonic fluid is accelerated through the divergent diffuser the pressure will decrease…

Q: 4-Steam flows through a device with a stagnation pressure of 120 psia, a stagnation temperature of…

A:

Q: An ideal gas with k = 1.4 is flowing through a nozzle such that the Mach number is 1.6 where the…

A: Given data: Initial Mach number, Ma1 = 1.6. The area at a Mach number of 1.6, A1 = 45 cm2. Final…

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: An air nozzle has an exit area 1.6 times the throat area. If a normal shock occurs at a plane where…

A: It will be assumed that the supply tank is large enough to be able to assume that the tank pressure…

Q: A gas initially at a subsonic velocity enters an adiabatic converging duct. Discuss how this affects…

A: (a). The velocity of the gas decreases.

Q: Products of combustion enter a gas turbine with a stagnation pressure of 0.90 MPa and a stagnation…

A: k = 1.33 R = 0.287 kJ/kg·K Calculate the power output of the turbine per unit mass flow…

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

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: Is it possible to accelerate a fluid to supersonic velocities with a velocity other than the sonic…

A: Given Supersonic velocities To find Acceleration of a fluid to supersonic velocities with a velocity…

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: how and why the stagnation enthalpy is defined? How does it differ from ordinary static enthalpy

A: The stagnation enthalpy h0 is defined as the sum of static enthalpy and kinetic energy. It is…

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

A: Bernoulli equation states that the sum of pressure energy , kinetic energy and potential energy and…

Q: A high-pressure air reservoir is connected to the inlet of a convergent-divergent nozzle as shown. A…

A:

Q: abcdefghikimnopqrstuvwxyz abcdefghjklmnopqrstuvwxyz abcdefghijklmnop yz A converging nozzle has a…

A: