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The Saturn V reached 400 feet per second (120 m/s) at over 1 mile (1,600 m) in altitude. Much of the early portion of the flight was spent gaining altitude, with the required velocity coming later. The Saturn V broke the sound barrier at just over 1 minute at an altitude of between 3.45 and 4.6 miles (5.55 and 7.40 km). At this point, shock ...
Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio ... Saturn V: Retired 1st RP-1 / ... 2.1: RD-864 15D177
C-1 – Saturn lower stage, proposed S-IV second stage (similar to the actual Saturn I). C-2 – Saturn lower stage, proposed S-II second stage, proposed S-IV third stage. C-3 , C-4 , and C-5 – all based on different variations of a new lower stage using F-1 engines, variations of proposed S-II second stages, and proposed S-IV third stages ...
During their two and a half minutes of operation, the five F-1s propelled the Saturn V vehicle to a height of 42 miles (222,000 ft; 68 km) and a speed of 6,164 mph (9,920 km/h). The combined flow rate of the five F-1s in the Saturn V was 3,357 US gal (12,710 L) [5] or 28,415 lb (12,890 kg) per second.
Jet or rocket engine Mass Thrust Thrust-to-weight ratio (kg) (lb) (kN) (lbf) RD-0410 nuclear rocket engine [1] [2]: 2,000 4,400 35.2 7,900 1.8 J58 jet engine (SR-71 Blackbird) [3] [4]
Diagram of Saturn V instrument unit. ... Weight at launch: ~4,400 lb (1996 kg) ... Includes documents on Saturn V, first stage, F-1 engine, second stage, J-2 engine ...
Payload (kg) ‡ First spaceflight § Last spaceflight Flights § Mercury ... Saturn IB Saturn V: 3: 8.5: 3.91: 5,500 CM + 14,700 LM + 24,500 Service Module: Fuel cells
The S-II (pronounced "S-two") was the second stage of the Saturn V rocket. It was built by North American Aviation. Using liquid hydrogen (LH2) and liquid oxygen (LOX) it had five J-2 engines in a quincunx pattern. The second stage accelerated the Saturn V through the upper atmosphere with 1,000,000 pounds-force (4.4 MN) of thrust.