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the maximum velocity of a rocket is approximated by: Delta_V = go*ISP*ln(Mi/Mf) where Delta_V = the change in velocity go = 32.2 ft/22 ISP = the specific impulse Mi = initial mass Mf = final mass mp = propellant mass mo = stage inert mass mf = stage total mass This equation has to be solved for each stage considering the masses of all of the fallowing stages and payloads Stage 1 mo (lb) 300000 mp (lb) 4492000 mf (lb) 4792000 Mi (lb) 6200600 Mf (lb) 1708600 ISP 263 delta V 10915.79 Stage 2 mo (lb) 95000 mp (lb) 942000 mf (lb) 1037000 Mi (lb) 1408600 Mf (lb) 466600 ISP 421 delta V 14977.96 Stage 3 mo (lb) 34000 mp (lb) 228000 mf (lb) 262000 Mi (lb) 371600 Mf (lb)143600 ISP 421 delta V 12889.05 payload mass (lb) 109600 Max Speed ft/s 38782.80 Max Speed Mph 26442.82 In short, ignoring aerodynamic friction and assuming a constant gravitation acceleration the maximum achievable velocity is about ~26500 mph