The engine was developed from the Mikulin AM-5 by redesigning the compressor. It was the first jet engine that was fully developed in the USSR and reached series production. In 1953 it passed its acceptance test with 25.5 kN (without afterburner).
The standard version RD-9B is a jet engine with a nine-stage axial compressor and a tubular ring combustion chamber with ten combustion tubes. An afterburner with a variable thrust nozzle has been added opposite the exit engine . The turbine is designed in two stages and is also flowed through axially. This version was produced in series from 1955. The acceleration time from idle to full power was up to 17 s.
- RD-9A and RD-9AK - versions without afterburner for the Jakowlew Jak-25 and Jakowlew Jak-26
- RD-9AF-300 and RD-9AF2-300 - versions with afterburner for the Jakowlew Jak-27 and Jakowlew Jak-28
- RD-9B - Version with afterburner for the MiG-19
- RD-9BF-811 - further developed version for the MiG-19
- RD-9FK - Version for the cruise missile K-10S
- Starting thrust with afterburner: 31.87 kN
- Starting thrust without afterburner: 25.5 kN
- Nominal thrust: 21.08 kN
- Travel thrust: 16.87 kN
- Specific consumption
- with afterburner: 1.6 kg / kph
- for travel services: 0.86 kg / kph
- Max. Speed: 11,150 min −1
- Turbine inlet temperature: 860 ° C
- Turbine outlet temperature: 680 ° C
- Air flow: 43 kg / s
- Compression: 7.2: 1
- Weight (dry): 700 kg
- Diameter: 670 mm
- Length: 5560 mm
- Jürgen Michels, Jochen Werner: Aviation East 1945–1990. History of German aviation in the Soviet occupation zone (SBZ) and the GDR. Bernard & Graefe, 1994, ISBN 3-7637-6109-8 .
- Bill Gunston: The Osprey Encyclopedia of Russian Aircraft: 1875-1995. Osprey, 1995, ISBN 1-85532-405-9 .