Encyclopedia Astronautica
Nova 8L Mod



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Nova NASA 8 F-1
Nova NASA 8 F-1 Modular
Credit: © Mark Wade
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Nova Concepts - NASA
Credit: © Mark Wade
American heavy-lift orbital launch vehicle. NASA Nova concept where first two stages use short Nova building blocks with 2 F-1's in each block. Four used in stage 1, one in stage 2. Typical of early Nova designs with F-1's in both first and second stages.

LEO Payload: 150,000 kg (330,000 lb) to a 160 km orbit. Payload: 50,000 kg (110,000 lb) to a translunar trajectory.

Stage Data - Nova 8L Mod

  • Stage 1. 4 x Nova 2 F-1 Module. Gross Mass: 1,134,000 kg (2,500,000 lb). Empty Mass: 77,000 kg (169,000 lb). Thrust (vac): 15,121.000 kN (3,399,336 lbf). Isp: 304 sec. Burn time: 200 sec. Isp(sl): 265 sec. Diameter: 10.10 m (33.10 ft). Span: 10.10 m (33.10 ft). Length: 28.70 m (94.10 ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: F-1. Status: Study, NASA, 1960. Comments: Short Nova building block. Four used in stage 1, one in stage 2.
  • Stage 2. 1 x Nova 2 F-1 Module. Gross Mass: 1,134,000 kg (2,500,000 lb). Empty Mass: 77,000 kg (169,000 lb). Thrust (vac): 15,121.000 kN (3,399,336 lbf). Isp: 304 sec. Burn time: 200 sec. Isp(sl): 265 sec. Diameter: 10.10 m (33.10 ft). Span: 10.10 m (33.10 ft). Length: 28.70 m (94.10 ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: F-1. Status: Study, NASA, 1960. Comments: Short Nova building block. Four used in stage 1, one in stage 2.
  • Stage 3. 1 x Nova 4 J-2. Gross Mass: 771,000 kg (1,699,000 lb). Empty Mass: 63,000 kg (138,000 lb). Thrust (vac): 3,559.000 kN (800,095 lbf). Isp: 420 sec. Burn time: 800 sec. Diameter: 10.10 m (33.10 ft). Span: 10.10 m (33.10 ft). Length: 38.10 m (124.90 ft). Propellants: Lox/LH2. No Engines: 4. Engine: J-2. Status: Study, NASA, 1960. Comments: Nova third stage.

Status: Study 1960.
Gross mass: 6,621,000 kg (14,596,000 lb).
Payload: 150,000 kg (330,000 lb).
Height: 115.00 m (377.00 ft).
Diameter: 10.10 m (33.10 ft).
Thrust: 52,727.50 kN (11,853,614 lbf).
Apogee: 160 km (90 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • F-1 Rocketdyne Lox/Kerosene rocket engine. 7740.5 kN. Isp=304s. Largest liquid rocket engine ever developed and flown. Severe combustion stability problems were solved during development and it never failed in flight. First flight 1967. More...
  • J-2 Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966. More...

See also
  • Nova Nova was NASA's ultimate launch vehicle, studied intently from 1959 to 1962. Originally conceived to allow a direct manned landing on the moon, in its final iteration it was to put a million-pound payload into low earth orbit to support manned Mars expeditions. It was abandoned in NASA advanced mission planning thereafter in favor of growth versions of the Saturn V. More...

Associated Manufacturers and Agencies
  • NASA American agency overseeing development of rockets and spacecraft. National Aeronautics and Space Administration, USA, USA. More...

Associated Stages
  • Nova 2 F-1 Module Lox/Kerosene propellant rocket stage. Loaded/empty mass 1,134,000/77,000 kg. Thrust 15,121.00 kN. Vacuum specific impulse 304 seconds. Short Nova building block. Four used in stage 1, one in stage 2. More...
  • Nova 4 J-2 Lox/LH2 propellant rocket stage. Loaded/empty mass 771,000/63,000 kg. Thrust 3,559.00 kN. Vacuum specific impulse 420 seconds. Nova third stage. More...

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