Modify Prob. 3.100 by accounting for air drags on the missile F CD2V2, where C 0.02, is the air density, D is the missile diameter,

Modify Prob. 3.100 by accounting for air drags on the missile F ≈ CρD2V2, where C ≈ 0.02, ρ is the air density, D is the missile diameter, and V is the missile velocity. Solve numerically for (a) the velocity and altitude at burnout and (b) the maximum altitude attained.