Difference between revisions of "Merlin"

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Latest revision as of 03:28, 15 October 2022

Merlin
Nopic.png
Overview
Vacuum thrust 409 kN
Sealevel thrust 342 kN
specific impulse (vac) 3.0 kN·s/kg
Fuel RP-1
Oxidizer LOX
Cycle gas-generator cycle
First flight 2006
Entered service Not in service
Manufacturer SpaceX
Dimensions
Length Unknown
Width Unknown
Dry mass approx. 400 kg
Power head
Chamber pressure 6.14 MPa
Chamber temperature Unknown
Fuel flow rate Unknown
Oxidizer flow rate Unknown

The Merlin engine is a RP-1/liquid oxygen gas-generator cycle rocket engine. The Merlin engine was developed for use on the Falcon 1, Falcon 5 and Falcon 9 rockets by SpaceX and is designed for sea recovery and reuse.

Engine details[edit]

The nozzle is an inexpensive, expendable ablatively cooled carbon fiber composite.

Engine revision 1B has been enhanced over the 1A with a turbine upgrade (from 1490 kW to 1860 kW)


Performance[edit]

Current published ratings:

General engine data
Manufacturer SpaceX
engine cycle gas-generator cycle
Performance
Sea level thrust 342 kN (77,000 lbf)
Vacuum thrust 409 kN (92,000 lbf)
Sea level Isp 2.6 kN·s/kg (255 s)
Vacuum Isp 3.0 kN·s/kg (304 s)
Chamber pressure 6.14 MPa (890 psi)
Propellants
Fuel RP-1 rocket grade kerosene
Oxidizer Liquid oxygen
Other information
Engine mass approx. 435 kg
Thrust-to-weight ratio (fully accounted) 96
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