1. A Rocket engine,equipped with a converging-diverging nozzle,burns
kerosene and liquid oxygen to produce nozzle entrance stagnation
conditions of 965psia,
6430 R.The oxygen-fuel ratio is 2.35 lbm oxygen/lbm kerosene,the
average molecular weight of the mixture of combustion products is 22
and the average specific heat ratio is 1.25. The engine is to produce
a net thrust of 1.5*1000000 lb at sea level design point exit 
conditions with atmospheric pressure equal to 15 psia.The net thrust
produced by a rocket engine is

             F = Mu + (p-p1)A
where
     F = net thrust,lb
     M = mass flow rate, slug/s
     u = nozzle exit velocity, ft/s
     p = nozzle exit pressure, lb/square ft
     p1 = back pressure on the nozzle, lb/square ft
     A = nozzle exit area, square ft

 As a first approach at specifying the nzzle dimensions and the oxygen
and fuel requirements,assume the flow of a perfect gas with the
average properties of the mixture,and neglect viscous,two-dimensional
flow,and heat transfer effects.
specify the following:

 a.  the nozzle throat area in square ft
 b.  the nozzle exit area in square ft
 c.  the mass flow rate of liquid oxygen in lbm/s
 d.  the mass flow rate of kerosene in lbm/s


NOTE : PLEASE GIVE ME THE SOLUTIONS(NUMERICAL VALUES) OF THE ABOVE
BITS.GIVE ME THE EQUATIONS TO GET THE SOLUTIONS.