Mathematical Modeling, Mathematical Optimization, Numerical Methods, Numerical Computation, Astrophysics.
{M_{R}}(t)=(0.05–0.002t)kg The rocket is assumed to start at 50 grams. Mass is variable so the expression becomes (M-\lambda*t)\\ $\lambda=\frac{dM_{R}}{dt}$=$-0.002$kg/sec\\ $M_{R}(1)=0.048kgs$ i.e 48 grams R=15 Newton k=0.02 which is the drag coefficient. Plugging the values in (2) we get (Check