Editing Merlin

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:

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


Performance:

Current published ratings:

    * Sea level thrust: 77,000 lbf (342 kN)
    * Vacuum thrust: 92,000 lbf (409 kN)
    * Chamber pressure: 6.14 MPa (890 psi)
    * Sea level Isp: 255 s (2.6 kN·s/kg)
    * Vacuum Isp: 304 s (3.0 kN·s/kg)
    * Thrust-to-weight ratio (fully accounted): 96

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


Operations:

    * Fuel: RP-1 rocket grade kerosene
    * Oxidizer: Liquid oxygen

[[Category:rocket engines]]
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-{{Infobox rocket engine|name=Merlin|thrust_vac=409 kN|thrust_sl=342 kN|isp_vac=3.0 kN·s/kg|cycle=[[gas-generator cycle]]|fuel=[[RP-1]]|oxidizer=[[LOX]]|first_flight_date=2006|service_date=Not in service|manufacturer=[[SpaceX]]|pc=6.14 MPa|dry_mass=approx. 400 kg}}
+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:
-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.
+The nozzle is an inexpensive, expendable [[ablatively cooled]] carbon fiber composite.
-==Engine details==
-The nozzle is an inexpensive, expendable [[Ablative cooling|ablatively cooled]] carbon fiber composite.
+Performance:
-Engine revision 1B has been enhanced over the 1A with a turbine upgrade (from 1490 kW to 1860 kW)
+Current published ratings:
+    * Sea level thrust: 77,000 lbf (342 kN)
+    * Vacuum thrust: 92,000 lbf (409 kN)
+    * Chamber pressure: 6.14 MPa (890 psi)
+    * Sea level Isp: 255 s (2.6 kN·s/kg)
+    * Vacuum Isp: 304 s (3.0 kN·s/kg)
+    * Thrust-to-weight ratio (fully accounted): 96
+Engine revision 1B has been enhanced over the 1A with a turbine upgrade (from 1490 kW to 1860 kW)
-==Performance==
-Current published ratings:
+Operations:
-{|
-|-
-!bgcolor="lightblue" colspan="2"|General engine data
-|-
-!Manufacturer
-|[[SpaceX]]
-|-
-![[engine cycle]]
-|[[gas-generator cycle]]
-|-
-!bgcolor="lightblue" colspan="2"|Performance
-|-
-!Sea level thrust
-|342 kN (77,000 lbf)
-|-
-!Vacuum thrust
-|409 kN (92,000 lbf)
-|-
-!Sea level I<sub>sp</sub>
-|2.6 kN·s/kg (255 s)
-|-
-!Vacuum I<sub>sp</sub>
-|3.0 kN·s/kg (304 s)
-|-
-!Chamber pressure
-|6.14 MPa (890 psi)
-|-
-!bgcolor="lightblue" colspan="2"|Propellants
-|-
-!Fuel
-|[[RP-1]] rocket grade kerosene
-|-
-!Oxidizer
-|[[Liquid oxygen]]
-|-
-!bgcolor="lightblue" colspan="2"|Other information
-|-
-!Engine mass
-|approx. 435 kg
-|-
-!Thrust-to-weight ratio (fully accounted)
-|96
-|-
-|}
+    * Fuel: RP-1 rocket grade kerosene
+    * Oxidizer: Liquid oxygen
-[[Category: Articles]]
+[[Category:rocket engines]]
-[[Category:Rocket engines]]
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