Evolution of the SpaceX Merlin-1 engine
(and parameter)
 

 

Engine

Merlin-1A

Merlin-1Ci

Merlin-1C

Merlin-1C+

Merlin-1D

Merlin-1D+ Merlin-1D++

Use

Falcon-1
(Demo)
Falcon-1
(interim upgrade)
Falcon-1e
Falcon-9 (B1)
Falcon-9 (B2)
(not realized)
Falcon-9 (v1.1) Falcon-9 (v1.2) Falcon-9 (v1.2)
(Block-5)
 

 


 


 


 


 



 



 

Propellant mix

2.17 2.17 2.17 2.17 2.34 2.36  

Net flow rate (kg)

130.50 133.16 161.39 202.44 236.63 298.70  

Thrust sea level

73,000 lbf

78,400 lbf 95,000 lbf 122,700 lbf 147,100 lbf 190,000 lbf 203,000 lbf

Thrust vacuum

83,000 lbf

88,700 lbf 108,500 lbf 138,800 lbf 166,900 lbf 205,500 lbf ?

Isp s.l. (sec)

253.7 264.5 267 275 282 288.5  

Isp vac (sec)

288.5 302.5 304.8 311 320 312  

Chamber pressure

5.39 MPa

6.08 MPa 6.14 MPa 6.77 MPa 9.72 MPa 10.8 MPa  

Pressure exp. rate

 ?

 ?

? ? 226 227  

Throat area (m2)

? ? ? ? 0.042 0.042  

Nozzle area (m2)

? ? ? ? 0.90 >0.90  

= Area exp. ratio

14.5 16 16 ? 21.4 >21.4  

Nozzle L/D (m)

- - - - - - -

 

Engine

Merlin-1CV

Merlin-1DV

Merlin-1DV+

Use

Falcon-9 (B1) Falcon-9 (v1.1) Falcon-9 (1.2)



 without nozzle extension



 


 

Propellant mix

2.17 2.36 2.38

Net flow rate (kg)

157.95 236.56 273.70

Thrust sea level

- - -

Thrust vacuum

117,000 lbf (?) 181,000 lbf 210.00 lbf

Isp s.l. (sec)

 - - -

Isp vac (sec)

336 347 348

Chamber pressure

6.14 MPa 9.72 MPa 10.8 MPa

Pressure exp. rate

 ? 3240 3170

Throat area (m2)

0.042 0.042 0.042

Nozzle area (m2)

4.90 4.90 >4.90

= Area exp. ratio

117 117 >117

Nozzle L/D (m)

2.70 x 2.50 2.70 x 2.50 >2.70 x 2.50