RD-9
Preserved Tumansky RD-9B turbojet engine
Type	Turbojet
Manufacturer	Tumansky
First run	1953
Major applications	Yak-25 MiG-19

The Tumansky RD-9 (initially designated Mikulin AM-5) was an early Soviet turbojet engine, not based on pre-existing German or British designs. The AM-5, developed by scaling down the AM-3,^[1] was available in 1952 and completed testing in 1953; it produced 25.5 kN (5,700 lb_f) thrust without afterburner. The AM-5 engine is notable for making possible the first mass-produced supersonic interceptors such as the MiG-19, and the first Soviet all-weather area interceptor, the Yak-25.^[2] When Sergei Tumansky replaced Alexander Mikulin as the OKB-24's chief designer in 1956, the engine was renamed RD-9.^{[citation needed]} The engine was later built under license in China as the WP-6.

Variants and applications

RD-9A

RD-9B

Used in the East German civilian jetliner project Baade 152 in 1958 and 1959, replaced when Pirna 014 engines became available.

RD-9AK

Non-afterburning versions for the Yak-25 and Yak-26.

RD-9AF-300

Afterburning version for the Yak-27 and Yak-28.

RD-9AF2-300

Afterburning version for the Yak-27 and Yak-28.

RD-9B

Afterburning version for the early variants of MiG-19.

RD-9BK

Version for Lavochkin La-17M.

RD-9BF-811

Afterburning version for the later variants of MiG-19.

RD-9V

Afterburning version used in the Ilyushin Il-40P.

WP-6

Chinese built version for the Shenyang J-6.

WP-6A

a Chinese upgraded version for the Nanchang Q-5 and J-6C.

WP-6Z

further developed for the cancelled Nanchang J-12

NK-TJ

^[i] North Korean version built for MiG-19 and Shenyang J-6^[3]

Specifications (RD-9BF-811)

Data from ^[4][5]

General characteristics

• Type: Afterburning turbojet
• Length: 5,560 mm (219 in)
• Diameter: 668 mm (26 in)
• Dry weight: 725 kg (1,600 lb)

Components

• Compressor: Single-spool 9-stage Axial compressor
• Turbine: axial flow

Performance

• Maximum thrust: 3,000 kgf (6,600 lbf, 29 kN) military power, 3,750 kgf (8,300 lbf, 37 kN) with afterburner
• Turbine inlet temperature: 860 °C
• Specific fuel consumption: 0.96 lb/(lbf⋅h) or 27 g/(kN⋅s) military power / 1.6 lb/(lbf⋅h) or 45 g/(kN⋅s) afterburner

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• Thrust-to-weight ratio: 5.2