Question
The maximum possible efficiency of a heat engine is ...........
$\eta=1-\frac{T_2}{T_1}$
So it depends on source and sink temperature.
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| Column $-I$ | Column $-II$ |
| $(A)$ Kinetic energy | $(p)$ $ - \frac{{G{M_E}m}}{{2r}}$ |
| $(B)$ Potential energy | $(q)$ $\sqrt {\frac{{G{M_E}}}{r}} $ |
| $(C)$ Total energy | $(r)$ $ - \frac{{G{M_E}m}}{{r}}$ |
| $(D)$ Orbital energy | $(s)$ $ \frac{{G{M_E}m}}{{2r}}$ |
(where $M_E$ is the mass of the earth, $m$ is mass of the satellite and $r$ is the radius of the orbit)