only question d). please help to convert the pseudocode to c++ code thanks

Roots of Non-linear Equations The upward velocity of a rocket can be computed by the following formula v=uln(m0qtm0)gt where v is the upward velocity, u is the velocity at which the fuel is expelled relative to the rocket, m0 is the initial mass of the rocket at time t=0,q is the fuel consumption rate and g is the downwards acceleration due to gravity. If u=2500m/s,m0=240,000kg,q=3650kg/s, and g=9.81m/s2, compute the time t at which v=1980m/s. Use single precision ( 6 significant digits) for all your manual calculations. Use the following methods a) Bisection method (manual calculations, starting points 5 and 55 , three iterations, single precision) b) False-position method (manual calc., starting points 5 and 55 , three iterations, single precision) c) Secant method (manual calculations, starting points 55 and 45 , three iterations, single precision) d) Newton-Raphson ( C++ program, use pseudocode, single precision (float), =0.0001,=0.01 ) e) Error analysis (compare a, b, c with d, respectively; express errors in percentage)