Tolong jelaskan mengenai Variants dari RL10

Thrust (altitude): 15,000 lbf (66.7 kN)

Engine weight - dry: 298 lb (135 kg)

Height: 68 in (1.73 m)

Diameter: 39 in (0.99 m)

Nozzle expansion ratio: 40 to 1

Propellants: Liquid Oxygen & Liquid Hydrogen

Propellant flow: 35 lb/s (16 kg/s)

Vehicle application: Saturn I / S-IV 2nd stage - 6-engines

Vehicle application: Centaur upper stage - 2-engines

Thrust (altitude): 24,750 lbf (110.1 kN)

Engine weight - dry: 610 lb (277 kg)

Height: 163 in (4.14 m)

Diameter: 87 in (2.21 m)

Expansion ratio: 250 to 1

Mixture ratio: 5.85 to 1

Propellants: Liquid oxygen & liquid hydrogen

Propellant flow: Oxidizer 41.42 lb/s (20.6 kg/s), fuel 7.72 lb/s (3.5 kg/s)

Vehicle application: Delta III, Delta IV second stage (1 engine)

The other current model, the RL10A-4-2, is the engine used on Centaur upper stage for Atlas V.