Velocity for a circular orbit at a height 2R above the earth (R is radius of the earth) is |

A) $√{{GM}/R}$ | B) $√{{2GM}/R}$ | C) $√{{GM}/{2R}}$ | D) $√{{GM}/{3R}}$ |

A satellite is in a circular orbit of radius 2R around the earth. At a certain point on its path a rocket fixed to the satellite is fired such that velocity of the satellite along the tangent increases. The resulting orbit of the satellite would be |

A) same as before |

B) circular orbit with radius greater than 2R |

C) elliptical orbit with minimum distance from the centre of earth equal to 2R |

D) elliptical orbit with maximum distance from the centre of earth equal to 2R |

A satellite at a height R above the earth has a velocity $√{{2gR}\/5}$ directed at right angles to line joining it to the center of the earth. Its orbit is |

A) elliptical with closest distance of 2R |

B) circular orbit of radius 2.4R |

C) elliptical with farthest distance of 2R |

D) circular orbit of radius 2R |

If a satellite in a circular orbit in the equatorial plane with a period of 24 hours were to rotate from east to west it would appear above a point on the equator at intervals of |

A) 24 hours | B) 12 hours | C) 8 hours | D) 6 hours |

A satellite in a circular orbit in the equatorial plane spinning from west to east appears above a certain point on the equator at intervals of 24 hours. If it were to spin in the opposite sense, this time interval would be |

A) 12 hours | B) 8 hours | C) 9 hours | D) 6 hours |

4,3,3,2,2