Question

the minimum period of revolution of an artifical satellite in a circular orbit round the earth.

G=
$6.67 \times 10 {}^{ - 11}$
Nm2/kg2.
R=
$6.4 \times {10}^{ 6} m$
M=
$6 \times {10}^{24} kg$





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Answer 1

Answer:

v(critical) = √GM/√(R+h)

after that t= 2πr/V(critical)