Abstract
Wikipedia's Raptor entry consolidates publicly-stated specifications and production-rate context. Raptor 3 (May 2026 update) at sea level: 250 tf nominal thrust (2.45 MN; 551,000 lbf), 1,525 kg mass, 330 bar chamber pressure, methalox propellant at 3.6 mixture ratio, full-flow staged combustion. Raptor 2 was 230 tf and 1,630 kg; Raptor 1 was 185 tf and 2,080 kg. Late-2022 SpaceX statements report production at "more than one Raptor a day" with the McGregor facility plus a planned second Texas site targeting "800 to 1,000 rocket engines each year." Marginal engine cost approached $1M in 2019; SpaceX's mass-production goal was "less than US$250,000" per engine at 500/yr scale. Engine reuse target is up to "1,000 flights" (aspirational, BFR program).
Key claims
- raptor-3-thrust-2026: "250 tf (2.45 MN; 551,000 lbf)" sea-level thrust per May 2026 update.
- raptor-isp-sea-level: ~330 s (Raptor 1), 347 s (Raptor 2) — methalox sea-level.
- raptor-production-target: "800 to 1000 rocket engines each year" target (McGregor + new Texas facility).
- raptor-cost-target: "less than US$250,000" per engine at 500/yr scale.
- raptor-reuse-target: "lifetime of 1000 flights" — aspirational, Musk statement.
- raptor-mixture-ratio: "3.6" LOX:LCH4 mixture ratio, consistent with Mobius and SDC anchor.
Reviewer notes
Tier E by classification but the consolidated specs are useful as a single-page anchor for the calc pass. Engine production is the binding constraint for expendable launch operations but not for reusable ones; for a reusable fleet of 500 vehicles flying 20 times each = 10,000 launches, engines needed are 500 × 39 = 19,500 total (one-time) plus replacement (5-10% per year) — well within "1,000/yr" production. The expendable extreme requires 10,000 × 39 = 390,000 engines/yr which is ~390× current target — implausible. Use as orientation; don't cite as evidence in claims; tier S/A and the primary press releases cited inside the Wiki entry are the citable substrates.