RS-84
Boeing Rocketdyne RS-84 was a canceled reusable hydrocarbon liquid rocket engine prototype. NASA identifies the LOX/RP-1 engine as an oxygen-rich staged-combustion design developed under the Next Generation Launch Technology and Rocket Engine Prototype efforts; a NASA comparison gives design values of 1,050 klbf (4,670.6 kN) sea-level thrust, 1,168 klbf (5,195.5 kN) vacuum thrust, and 301.5/335.4 s sea-level/vacuum specific impulse. The development program was canceled before a flight installation, so these are design values rather than flown performance.
Identity
- Aliases
- RS-84Boeing Rocketdyne RS-84
- Domains
- spaceflight
- Identity Level
- model
- Kind
- liquid-rocket-engine
- Name
- RS-84
- Status
- historical
Details
- Description
- Boeing Rocketdyne RS-84 was a canceled reusable hydrocarbon liquid rocket engine prototype. NASA identifies the LOX/RP-1 engine as an oxygen-rich staged-combustion design developed under the Next Generation Launch Technology and Rocket Engine Prototype efforts; a NASA comparison gives design values of 1,050 klbf (4,670.6 kN) sea-level thrust, 1,168 klbf (5,195.5 kN) vacuum thrust, and 301.5/335.4 s sea-level/vacuum specific impulse. The development program was canceled before a flight installation, so these are design values rather than flown performance.
- Developers
- Manufacturers
- Propellants
- liquid oxygenRP-1
- Rocket Specs
- Cycle
- oxygen-rich staged combustion
- Sea Level Specific Impulse
- …
- Sea Level Thrust
- …
- Vacuum Specific Impulse
- …
- Vacuum Thrust
- …
Links
- Official Url
- https://ntrs.nasa.gov/citations/20030066142
Assets & Meta
- Creation Time
- August 14, 2026 at 23:23:58 UTC
- Updated Time
- August 22, 2026 at 07:05:26 UTC
Other
- Sources
- Accessed Date
- 2026-08-14
- Note
- NASA identifies RS-84 as the Boeing Rocketdyne NGLT concept using oxygen-rich staged combustion with oxygen and RP-1 propellants.
- Publisher
- NASA Technical Reports Server
- Title
- RS-84 Engine
- Accessed Date
- 2026-08-14
- Note
- NASA records the RS-84 as a roughly 1-million-lbf-class reusable LOX/kerosene booster prototype and states that the effort was canceled.
- Publisher
- NASA Technical Reports Server
- Title
- Joint Propulsion Conference and Exhibit: RS-84 Engine Development Test Program
- Accessed Date
- 2026-08-22
- Note
- NASA's liquid-propulsion comparison lists RS-84 design values of 1,050/1,168 klbf sea-level/vacuum thrust and 301.5/335.4 s sea-level/vacuum specific impulse; the normalized kN values are stored in rocketSpecs.
- Publisher
- NASA Technical Reports Server
- Title
- Liquid Propulsion Systems - Evolution and Advancements