The RD-8 engine was developed by Yuzhnoye Design Bureau for the second stage of the Zenit rocket. It has four hinged chambers and a single turbopump unit. The fuel pair is LOX/kerosene. Vacuum thrust is 78.5 kN and its specific impulse in vacuum is 342 seconds (3.35 km/s).
The engine was designed for long service life (up to 4000 seconds), high reliability, and is the first smaller upper stage engine to use the staged combustion cycle.