The tangential velocity component ' $V$ of a spacecraft, which is in a circular orbit of radius ' $R$ ' around a spherical Earth $(\mu=\mathrm{GM} \rightarrow$ gravitational parameter of Earth) is given by the following expression.
(A) $V=\sqrt{\frac{\mu}{2 R}}$
(B) $V=\sqrt{\frac{\mu}{R}}$
(C) $V=\frac{2 \pi}{\sqrt{\mu}} R^{\frac{3}{2}}$
(D) $V=\frac{2 \pi}{\sqrt{\mu}} R^{\frac{2}{3}}$
The tangential velocity component ' $V$ of a spacecraft, which is in a circular orbit of radius ' $R$ ' around a spherical Earth $(\mu=\mathrm{GM} \rightarrow$ gravitational parameter of Earth) is given by the following expression.
(A) $V=\sqrt{\frac{\mu}{2 R}}$
(B) $V=\sqrt{\frac{\mu}{R}}$
(C) $V=\frac{2 \pi}{\sqrt{\mu}} R^{\frac{3}{2}}$
(D) $V=\frac{2 \pi}{\sqrt{\mu}} R^{\frac{2}{3}}$