Nova B - Credit: © Mark Wade. 1,834 bytes. 52 x 428 pixels.

Convair/Ehricke Nova design using standard tank/engine modules of 4.9 m diameter in both first and second stages; 6 F-1 engine/modules in first stage, 6 J-2 engine/modules in second stage.

LEO Payload: 112,000 kg. to: 556 km Orbit. at: 0.0 degrees. Payload: 47,000 kg. to a: escape trajectory. Liftoff Thrust: 4,081,350 kgf. Total Mass: 2,806,400 kg. Core Diameter: 12.2 m. Total Length: 84.0 m.

• Stage Number: 1. 1 x Nova B-1 Gross Mass: 1,995,000 kg. Empty Mass: 100,000 kg. Thrust (vac): 4,682,000 kgf. Isp: 304 sec. Burn time: 121 sec. Isp(sl): 265 sec. Diameter: 12.2 m. Span: 12.2 m. Length: 28.0 m. Propellants: Lox/Kerosene No Engines: 6. F-1

• Stage Number: 2. 1 x Nova B-2 Gross Mass: 614,000 kg. Empty Mass: 38,000 kg. Thrust (vac): 1,043,000 kgf. Isp: 420 sec. Burn time: 228 sec. Isp(sl): 150 sec. Diameter: 12.2 m. Span: 12.2 m. Length: 23.8 m. Propellants: Lox/LH2 No Engines: 7. J-2

• Stage Number: 3. 1 x Nova B-3 Gross Mass: 63,000 kg. Empty Mass: 5,000 kg. Thrust (vac): 46,000 kgf. Isp: 427 sec. Burn time: 533 sec. Diameter: 6.7 m. Span: 6.7 m. Length: 18.3 m. Propellants: Lox/LH2 No Engines: 7. RL-10

• 45 - Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961.