Answer:
- <u>36% of the initial heat can be used to do work.</u>
Explanation:
The initial heat is the 100%, i.e. it is all the heat that will be transferred.
It wil be transferred into two different kinds of energy:
- additional thermal energy that will increase the thermal energy of the gas, making it hotter. Call it U. U = 64%. And,
- "fuel" for the gas to do work. Call it W.
Then,
That is, 36% of the initial heat is available to do work.
The answer is A i thing im not sure
Answer:
I think it would be C since it doesn't say anything about the gravity, basically things around u change, but you don't change
Explanation:
Sorry if I got this wrong, hope this helped and have a nice day!
Answer;
- Nuclear fusion
Explanation;
-Hydrogen bombs and stars both produce energy with the nuclear fusion. On other side, the Sun and other stars make heat and light by nuclear reactions.
-The first stage of a hydrogen bomb involves a fission explosion which in turn leads to a nuclear fusion. The extreme heat and pressure from the initial atomic blast force together deuterium and tritium (two light gases made of hydrogen). When they are forced together, some of the hydrogen atoms fuse to one another, creating helium.
-This process of fusion releases even more energy per unit of mass than fission does, and the energy released from the fusion reaction also feeds back into the fission reaction, increasing its output.
Answer:
Explanation:
We know that , for an object to remain in circular motion , a force towards centre is required which is called centripetal force. In the circular motion of
satellites around planet , this force is provided by the gravitational attraction between satellite and planet.
If M be the mass of planet and m be the mass of satellite, G be gravitational constant and R be the distance between planet and satellite or R be the radius of orbit
Gravitational force = G Mm / R²
If v be the velocity with which satellite is orbiting
centripetal force
= m v² /R
Centripetal force = gravitational attraction
m v² /R = G Mm / R²
v =
Time period = time the satellite takes to make one rotation
= distance / orbital velocity
= 2πR/ v
=
T =