L37.5 liquid rocket engine
Historical ISRO L37.5 liquid rocket engine identified by the GSLV-D1 mission reference as the single engine powering the GS2 second stage of the original GSLV configuration. The same official stage table records UDMH/N2O4 propellants, 720 kN maximum vacuum thrust, 150-second burn, and 2890 N·s/kg specific impulse (294.7 s); no later GSLV Vikas installation is inferred here.
Identity
- Aliases
- L37.5L-37.5
- Domains
- spaceflight
- Identity Level
- model
- Kind
- liquid-rocket-engine
- Name
- L37.5 liquid rocket engine
- Status
- historical
Details
- Description
- Historical ISRO L37.5 liquid rocket engine identified by the GSLV-D1 mission reference as the single engine powering the GS2 second stage of the original GSLV configuration. The same official stage table records UDMH/N2O4 propellants, 720 kN maximum vacuum thrust, 150-second burn, and 2890 N·s/kg specific impulse (294.7 s); no later GSLV Vikas installation is inferred here.
- Developers
- First Flight Date
- 2001-04-18
- Manufacturers
- Propellants
- UDMHdinitrogen tetroxide
- Rocket Specs
- Burn Time
- …
- Vacuum Specific Impulse
- …
- Vacuum Thrust
- …
Links
- Official Url
- https://www.isro.gov.in/mission_GSLV_D1.html
Assets & Meta
- Creation Time
- August 15, 2026 at 05:58:19 UTC
- Updated Time
- August 20, 2026 at 10:19:42 UTC
Other
- Sources
- Accessed Date
- 2026-08-14
- Note
- Names the single L37.5 engine for the GS2 second stage and records UDMH/N2O4 propellants, 720 kN maximum vacuum thrust, 150-second burn, and 2890 N·s/kg specific impulse for that engine; 2890 N·s/kg is represented as 294.7 s using standard gravity.
- Publisher
- Indian Space Research Organisation
- Title
- GSLV-D1 / GSAT-1