Nova NASA 6 F-1 Credit - © Mark Wade Media Gallery

The Nova vehicle most often illustrated in the popular press and histories. As in other early concepts, this NASA design of 1959/1960 used F-1 engine in both first and second stages. Resulting performance and total liftoff mass was equivalent to later Saturn V.

Manufacturer: NASA. LEO Payload: 132,000 kg (291,000 lb). to: 160 km Orbit. Payload: 45,000 kg (99,000 lb). to a: translunar trajectory. Liftoff Thrust: 39,865.100 kN (8,962,031 lbf). Total Mass: 3,152,400 kg (6,949,800 lb). Core Diameter: 14.60 m (47.90 ft). Total Length: 66.00 m (216.00 ft).

• Stage Number: 1. 1 x Stage: Nova NASA-1. Gross Mass: 2,268,000 kg (5,000,000 lb). Empty Mass: 113,000 kg (249,000 lb). Thrust (vac): 45,914.000 kN (10,321,877 lbf). Isp: 296 sec. Burn time: 134 sec. Isp(sl): 257 sec. Diameter: 14.60 m (47.90 ft). Span: 14.60 m (47.90 ft). Length: 31.40 m (103.00 ft). Propellants: Lox/Kerosene. No Engines: 6. Engine: F-1. Status: Study 1959.

• Stage Number: 2. 1 x Stage: Nova NASA-2. Gross Mass: 499,000 kg (1,100,000 lb). Empty Mass: 35,000 kg (77,000 lb). Thrust (vac): 7,640.000 kN (1,717,540 lbf). Isp: 304 sec. Burn time: 177 sec. Isp(sl): 265 sec. Diameter: 9.80 m (32.10 ft). Span: 9.80 m (32.10 ft). Length: 12.50 m (41.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: F-1. Status: Study 1959.

• Stage Number: 3. 1 x Stage: Nova NASA-3. Gross Mass: 227,000 kg (500,000 lb). Empty Mass: 21,000 kg (46,000 lb). Thrust (vac): 2,667.000 kN (599,565 lbf). Isp: 420 sec. Burn time: 313 sec. Isp(sl): 150 sec. Diameter: 9.80 m (32.10 ft). Span: 9.80 m (32.10 ft). Length: 11.00 m (36.00 ft). Propellants: Lox/LH2. No Engines: 4. Engine: J-2. Status: Study 1959.

• Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961. The only such comprehensive handbook ever produced, and at the dawn of the space age.