Take v = velocity given to satellite in its orbit v_(0) = sqrt((GM)/(R )), v_(e ) = escape velocity {:("Column-I",,"Column-II"),((A) v= V_(0),,"(P) Elliptical path"),((B) v_(0) lt v lt v_(e),,"(Q) Hyperbolic path"),((C) v = v_(e),,"(R) Circular path"),((D) v gt v_(e ),,"(S) Parabolic path"):}

Take v = velocity given to satellite in its orbit v_(0) = sqrt((GM)/(R

1.	Take v = velocity given to satellite in its orbit v_(0) = sqrt((GM)/(R )), v_(e ) = escape velocity {:("Column-I",,"Column-II"),((A) v= V_(0),,"(P) Elliptical path"),((B) v_(0) lt v lt v_(e),,"(Q) Hyperbolic path"),((C) v = v_(e),,"(R) Circular path"),((D) v gt v_(e ),,"(S) Parabolic path"):}
Answer» ANSWER :A-R; B-P; C-S; D-Q