Calculate the Mach number of the exit if the diverging duct has an inlet area and velocity of air of 0.5m^2 and 60 m/s respectively. The exit area is 8 times the inlet, and the temperature on the exit is standard atmospheric valu
Q: What is the Mach number?
A: To find Mach number
Q: PROBLEMS 1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making…
A:
Q: A shock wave moves at Mach 1.5 into a closed pipe in which the air is initially at 300K and 101325…
A: Shock wave is something which is defined as movement of any fluid at a speed more that the speed of…
Q: Calculate the Mach number of the exit if the diverging duct has an inlet area and velocity of air of…
A: Given:- Inlet area = 0.5 m2 Inlet velocity = 60 m/s Outlet area = 8×0.5 = 4 m2 To Find :- Mach…
Q: Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.6. If the…
A: Given data
Q: For a converging-diverging nozzle that is choked what is the ratio of nozzle area divided by the…
A:
Q: Read the question carefully and Give me right solution according to the question. Air flow over a…
A: Given: The mach number before shock, Mx = 1.5 The static pressure before shock, Px = 40 kPa The…
Q: Consider gas flow through a converging–diverging nozzle. Of the five following statements, select…
A: Converging – diverging nozzle. It is used to accelerate or deaccelerate the flow depending upon the…
Q: What is the Mach Number of an aircraft flying at 3000 ft with 450 m/s? What is the aspect ratio of…
A:
Q: A supersonic converging-diverging nozzle has an exit-to-throat area ratio of 1.555. The flow at the…
A:
Q: Question Four Air enters a pipe at a Mach number of 2.5, a temperature of 400 °C and a pressure of…
A:
Q: In March 2004, NASA successfully launched an experimental supersonic-combustion ramjet engine…
A: Given Data: The Mach of the scramjet is: M=7 The temperature is: T=-45 °F
Q: [5] An experimental centrifugal compressor is fitted with free-vortex guide vanes in order to reduce…
A:
Q: Q.2 Air which enters a diverging duct is slowed by a normal shock wave, as shown in figure. The…
A:
Q: Q9: A normal shock wave is propagated into still air with a velocity of 722.4 m/s. The still air…
A: "Since you have posted a question with multiple sub-parts, we will solve first three sub parts for…
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: Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.5. If the…
A: Given data P1=10 psiaT1=440.5 R
Q: Q.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C…
A: Given data: The inlet temperature is T1=500 °C. The inlet Pressure is P1=500 kPa The heat loss rate…
Q: Consider the isentropic flow through a convergent-divergent nozzle with an exit-to-throat area ratio…
A:
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: 11.47 At a certain point in a pipe, air flows steadily with a velocity of 150 m/s and has a static…
A: Given Data The velocity of air is:v=150 m/s The static pressure is:P=45 kPa The static temperature…
Q: Air having a reservoir pressure of 30 psia and density of 0.15 lb/ft is accelerated to a Mach number…
A:
Q: What is the mass flow rate of air at the exit if the inlet has a Mach number of 0.45, an area of…
A:
Q: The design pressure ratio of a steam turbine nozzle is 0.185. It operates at an off-design condition…
A:
Q: Consider the isentropic flow through a supersonic wind-tunnel nozzle. The reservoir properties are…
A: Given data: T0=500 KP0=10 atmH=9522 ft Need to determine the the exit temperature and density.
Q: In March 2004, NASA successfully launched an experimental supersonic-combustion ramjet engine…
A: Given data: Mach number for the jet engine, Ma = 7. The temperature of the air, T = -50°C. The…
Q: D5. A converging-diverging nozzle operates with air and subsonic flow at the inlet and supersonic…
A: Find , M2 , P2 at exit
Q: The tunnel exhausts to the ambient environment, where the back pressure is Patm. The starting…
A: With just tunnel mach numbers of 1.5, 2 and 3 and test section cross sectional areas of 6×6 and…
Q: An air stream with a Mach number of (3.04) a pressure of (302 kPa) and a temperature of (502 K)…
A:
Q: Example: Carbon dioxide flows steadily at a mass flow rate of 3 kg/s and pressure of 1400 kPa and…
A:
Q: The ratio of stagnation temperature at the exit and entry of a combustion chamber is 3.75. If the…
A:
Q: 1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle…
A:
Q: Nitrogen enters a converging–diverging nozzle at 620 kPa and 310 K with a negligible velocity, and…
A: Given: Initial pressure, P01=620 kPa Initial temperature, T01=310 K Upstream Mach no., Ma1=3…
Q: A high-flying jet cruising at 3000km/hr displays a Mach Number of 3.2. What is the speed of sound…
A: Speed of jet v=3000 km/hrv=3000×518 =833.33 m/sec M=3.2 Mach number is defined as the ratio of flow…
Q: For a given Prandtl-Meyer expansion, the upstream Mach number is 3 and the pressure ratio across the…
A: Stagnation point: The point at which the velocity of the fluid becomes zero. When the fluid is…
Q: Nitrogen discharges isentropically through a nozzle from a reservoir. The pressure from section 1 of…
A: Nozzle is a device which having varying in cross section, in which pressure is reduced by expansion.…
Q: -Consider the isentropic flow through a converging diverging nozzle with an exit to throat area…
A: Please find the solution below
Q: A converging-diverging nozzle is supplied with air from a reservoir where the pressure and…
A:
Q: Calculate the Mach number of the exit if the diverging duct has an inlet area and velocity of air of…
A: The mach number and area ratio relation can be given as - A2A12 = 1M22γ+11+γ-12M2γ+1γ-182 =…
Q: Air is expanded from 200 kPa and 500°K through a throat to an exit Mach number of 2.5. If the…
A: Assume, P0=200 kPaT0=500 KP*=528 P0=105.7 kPaT*=T01.2=416.6 Kρ*=P*RT*=105.7×103287×416.6=0.884…
Q: An air tank with a nozzle, has a pressure of twice the standard sea level pressure and density of…
A: Tank Pressure, P0 = 2×101.325 kPa = 204.65 kPa The density of the air in the tank, ρ0 = 2.45 kgm3…
Q: Air enters a nozzle at 0.2 MPa, 350 K, and a stagnation velocity. Assuming isentropic flow,…
A:
Q: aircraft flies with a Mach number Ma1=0.962 at an altitude of 7062 m where the pressure is 46.2 kPa…
A:
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: 94. 6.16. Nitrogen flows through a converging-diverging nozzle designed to operate at a Mach number…
A:
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.…
Calculate the Mach number of the exit if the diverging duct has an inlet area and velocity of air of 0.5m^2 and 60 m/s respectively. The exit area is 8 times the inlet, and the temperature on the exit is standard atmospheric value.
Trending now
This is a popular solution!
Step by step
Solved in 3 steps