Klimov RD-33

Twin-shaft afterburning turbofan (two per aircraft) developed under S.P. Izotov for the MiG-29, and license-built in Russia and China as the RD-93 variant with a shifted gearbox for single-engine airframes like the JF-17 Thunder. Manufacturer and state-sourced figures below carry limited independent verification.

In service since 1982

Compiled from public sources ·primary reference ↗ ·last verified 2026-08-10

kN thrust

1,055

7.87

T/W

Several performance figures for Russia-origin systems are manufacturer or state claims with limited independent verification. Treat these specs as directional, not tested values.

Procurement snapshot

Availability & export

Russian state channel

Rosoboronexport monopoly; Western sanctions exposure and payment/logistics risk for many buyers.

Channel: Rosoboronexport (state)

Fielded & proven

Operator data not public

In service since 1982. Status: active.

Lifecycle cost (est.)

No public unit price to model from. Why so few systems publish one →

Interoperability

No standardised NATO calibre / datalink detected in public specs.

Derived guidance from public data, export regime by country of origin, lifecycle from the GAO ~30% acquisition rule. Verify eligibility, pricing and offsets with the manufacturer and your acquisition authority.

Overview

The upgraded RD-33MK fitted to the MiG-35 raises afterburning thrust to a reported 88 kN (9,000 kgf), adds FADEC digital control and eliminates the visible smoke trail of earlier RD-33 production, at a slightly higher dry weight of roughly 1,145 kg. Treat all figures as Russian manufacturer/state claims given the Russia origin caveat applied sitewide.

Powers these platforms

Systems in the WeaponSpecs database that list the Klimov RD-33 as their engine.

MiG-29

MiG-35

Full specifications

Performance

Speed, range, altitude and engagement capability.

Performance specifications
Thrust-to-weight Engine thrust divided by loaded weight. Above 1.0 the aircraft can accelerate going straight up. On a standalone engine record, this is the engine's own thrust divided by its dry weight, the standard figure of merit for jet engines.	7.87 Stronger than 39% of engines

Physical

Dimensions, weight and crew.

Physical specifications
Length Overall length including gun/probe where applicable.	4.23 m
Width Overall width, matters for rail/road transport of vehicles.	1.04 m
Empty weight Weight without fuel, ammunition or crew.	1,055 kg

Propulsion

Engine, power and fuel.

Propulsion specifications
Thrust Total engine thrust (with afterburner where applicable).	81 kN Stronger than 25% of engines
Propulsion type Turbofan, turboshaft, diesel, gas turbine, solid-fuel rocket, ramjet…	Afterburning turbofan

Specifications compiled from public JSC Klimov and reference sources ↗. Published defense figures are approximations, treat comparisons as directional. Last verified 2026-08-10.

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