Answer:
a. The very first liquid process, when heated from 1250 degree Celsius, is expected to form at the temperature by which the vertical line crosses the phase boundary (a -(a + L)) which is about <em>1310 degree Celsius. </em>
b. The structure of that first liquid is identified by the intersection with ((a+ L)-L) phase boundary; <em>47wt %of Ni</em> is of a tie line formed across the (a+ L) phase area <em>at 1310 degrees.</em>
c. To find the alloy's full melting, it is determined that the intersection of the same vertical line at 60 wt percent Ni with (a -(a+L)) phase boundary is around <em>1350 degrees.</em>
c. The structure of the last remaining solid before full melting correlates to the intersection with the phase boundary (a -(a + L), of the tie line built at 1350 degrees across the (a + L) phase area, <em>being 72wt % of Ni.</em>
Answer:
Market Researcher
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Credit Analyst
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Explanation:
Answer:
Exit velocity
m/s.
Explanation:
Given:
At inlet:

Properties of steam at 100 bar and 600°C

At exit:Lets take exit velocity 
We know that if we know only one property inside the dome then we will find the other property by using steam property table.
Given that dryness or quality of steam at the exit of nozzle is 0.85 and pressure P=80 bar.So from steam table we can find the other properties.
Properties of saturated steam at 80 bar

So the enthalpy of steam at the exit of turbine



Now from first law for open system

In the case of adiabatic nozzle Q=0,W=0

m/s
So Exit velocity
m/s.
Answer:

Explanation:
Let assume that changes in gravitational potential energy can be neglected. The fire hose nozzle is modelled by the Bernoulli's Principle:

The initial pressure is:

The speed at outlet is:

![v=\frac{(250\,\frac{gal}{min} )\cdot (\frac{3.785\times 10^{-3}\,m^{3}}{1\,gal} )\cdot(\frac{1\,min}{60\,s} )}{\frac{\pi}{4}\cdot [(1.125\,in)\cdot(\frac{0.0254\,m}{1\,in} )]^{2} }](https://tex.z-dn.net/?f=v%3D%5Cfrac%7B%28250%5C%2C%5Cfrac%7Bgal%7D%7Bmin%7D%20%29%5Ccdot%20%28%5Cfrac%7B3.785%5Ctimes%2010%5E%7B-3%7D%5C%2Cm%5E%7B3%7D%7D%7B1%5C%2Cgal%7D%20%29%5Ccdot%28%5Cfrac%7B1%5C%2Cmin%7D%7B60%5C%2Cs%7D%20%29%7D%7B%5Cfrac%7B%5Cpi%7D%7B4%7D%5Ccdot%20%5B%281.125%5C%2Cin%29%5Ccdot%28%5Cfrac%7B0.0254%5C%2Cm%7D%7B1%5C%2Cin%7D%20%29%5D%5E%7B2%7D%20%7D)

The initial pressure is:


Answer:
ur answer friend
Explanation:
answer
<em>S</em><em>o</em><em>l</em><em>i</em><em>d</em><em>-</em><em>F</em><em>u</em><em>e</em><em>l</em><em> </em><em>R</em><em>o</em><em>c</em><em>k</em><em>e</em><em>t</em><em> </em><em>-</em><em> </em>a solid-propellant rocket or solid rocket is a rocket with a rocket engine that uses solid propellants. The earliest rockets were solid-fuel rockets powered by gunpowder; they were used in warfare by the Chinese, Indians, Mongols and Persians, as early as 13th century.
<em>L</em><em>i</em><em>q</em><em>u</em><em>i</em><em>d</em><em>-</em><em>F</em><em>u</em><em>e</em><em>l</em><em> </em><em>R</em><em>o</em><em>c</em><em>k</em><em>e</em><em>t</em><em> </em><em>-</em><em> </em>a liquid-propellant rocket or liquid rocket utilizes a rocket engine that use liqiud propellants. An inert gas stored in a tank at a high pressure is sometimes used instead of pumps in simpler small engines to force the propellants into the combustion chamber.
<em>I</em><em>o</em><em>n</em><em> </em><em>R</em><em>o</em><em>c</em><em>k</em><em>e</em><em>t</em><em> </em><em>-</em><em> </em>an ion thruster or ion drive is a form of electric propulsion used for spacecraft propulsion. It creates thrust by accelerating ions using electricity. The Deep Space 1 spacecraft, powered by an ion thruster, changed velocity by 4.3 km/s ( 9600 mph ) while consuming less than 74 kg ( 163 lb ) of xenon.
<em>P</em><em>l</em><em>a</em><em>s</em><em>m</em><em>a</em><em> </em><em>R</em><em>o</em><em>c</em><em>k</em><em>e</em><em>t</em><em> </em><em>-</em><em> </em>in this type of rocket, a combination of electric and magnetic fields are used to break down the atoms and molecules of a propellant gas into a collection of particles that have either a positive charge (ions) or a negative charge (electrons). In other words, the propellant gas becomes a plasma.
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