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Supersonic flow is produced in a de laval nozzle by constricting the flow in the center in order to increase the velocity. The shape will be hour-glass in nature. The initial mass flow rate and inlet pressure must be sufficient to produce a supersonic choked flow and the discharge pressure must be sufficiently low enough for supersonic flow to occur.
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The test section RHOMBUS of a supersonic wind tunnel makes flow uniform in test section?
Using shock-expansion cancellation technique flow in the diverging part of a supersonic nozzle is brought back to free stream direction ( direction parallel to the axis of nozzle) where a rhombus shaped region(Test Section) is formed in which uniform flow is ensured. Refer Method Of Characteristics from Rathakrishnan For Diagram.
How does a wedco model 40730 nozzle work?
The Wedco Nozzle is a CARB compliant spill-proof gas can nozzle. With the nozzle in place you can invert your gas can and it will not leak. Then simply push the nozzle lock and push the nozzle against the rim of the filling throat of the tank you're filling to start the flow of fuel. If you lift the nozzle away from the rim the flow stops.
What is critical pressure in nozzle?
Critical pressure in a nozzle is the pressure at which the flow of material through the nozzle reaches its maximum. Beyond which any increase in pressure will not result in an increase in flow. The point at which the velocity of a fluid in the throat of the nozzle reaches the local speed of sound, creating a sonic wave, or a sonic choke.
what is purpose of nozzle in steam turbine?
It sends hot gases from the combustion chamber to the 1st stage turbine blades at the correct angle and speed
What is the Tangential flow in turbine?
When flow of water on turbine is tangential, flow is tangential flow
What are the advantages and disadvantages of flow nozzle?
One disadvantage in the convergent-divergent nozzle as a shock wave can take place in the nozzle A nozzle is a device that converts pressure energy to kinetic energy (increasing fluid velocity on the account of static pressure) For a convergent nozzle there is no disadvantages as it can raise the fluid velocity only for the sonic speed the convergent-divergent type raises the velocity to over than sonic speed making supersonic flow, this could make a shock wave in the nozzle that turns the supersonic flow to subsonic flow
What is the difference between divergent nozzle and diffuser?
too bad i dont know what either of those are
The test section RHOMBUS of a supersonic wind tunnel makes flow uniform in test section?
Using shock-expansion cancellation technique flow in the diverging part of a supersonic nozzle is brought back to free stream direction ( direction parallel to the axis of nozzle) where a rhombus shaped region(Test Section) is formed in which uniform flow is ensured. Refer Method Of Characteristics from Rathakrishnan For Diagram.
Why does a gas flowing supersonically in Laval nozzle continue to accelerate even though the flow area is increasing in the divergent section of the nozzle?
In the converging section of the nozzle,relatively high pressure expanding has a small increase in specific volume. At lower pressures the increase in specific volume is large.
In divergent nozzle pressure will increase or decrease?
In a divergent nozzle, pressure will decrease as the flow area increases. This is due to the conservation of mass principle, where an increase in area causes a decrease in velocity and thus a decrease in pressure according to Bernoulli's equation.
What has the author A H Lange written?
A. H. Lange has written: 'Measurement of boundary-layer transition on a standard model to determine the relative disturbance level in two supersonic wind tunnels' 'Pressure and temperature measurements of the flow produced by a 12 x 12 cm grating nozzle'
Why mach number 1 at throat section of converging diverging nozzle?
At Mach number 1 at the throat section of a converging-diverging nozzle, the flow is said to be choked. This occurs when the flow velocity reaches the local speed of sound, leading to a critical point where the mass flow rate cannot increase any further. The design of the nozzle is crucial to achieving this critical condition for optimal performance in applications such as rocket engines and supersonic aircraft.
What has the author G T Golesworthy written?
G. T. Golesworthy has written: 'The performance of a conical convergent-divergent nozzle with area ratio 2.9 in external flow' -- subject(s): Supersonic nozzles
What are the characteristics and applications of supersonic flow?
Supersonic flow is characterized by speeds faster than the speed of sound. It is often used in applications such as supersonic aircraft, missiles, and high-speed wind tunnels. Supersonic flow can create shock waves and high temperatures, making it challenging to control and design for.
How does a wedco model 40730 nozzle work?
The Wedco Nozzle is a CARB compliant spill-proof gas can nozzle. With the nozzle in place you can invert your gas can and it will not leak. Then simply push the nozzle lock and push the nozzle against the rim of the filling throat of the tank you're filling to start the flow of fuel. If you lift the nozzle away from the rim the flow stops.
Who flow the first supersonic?
Chuck Yeager did in 1947.
What are the effects on the air flowing over aerodynamic surfaces when travelling at subsonic and supersonic speeds?
At subsonic speeds air acts like a fluid and Bernoulli's principals apply, at supersonic speeds, air acts like a gas (it's compressed). At subsonic speed, air speed increases with a decrease in area and vice versa. Above the sound barrier, air speed decreases with a decrease in area. This does not seem logical or intuitive. As the subsonice air flow through test chamber at near speed of sound and the area decreases at the nozzle, the airflow increases and a shock wave developes. Aft of the shock wave, the air is now supersonic. Then as the nozzle opens wider, the flow continues to increase in speed until a time when the pressure is insufficient to support the flow---then another shock waves developes as the flow drops back to sub-sonic.
