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Template:Engine thrust to weight table

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This is an old revision of this page, as edited by SCΛRECROW (talk | contribs) at 10:24, 15 April 2010 (Added J-58 engine weight + ref). The present address (URL) is a permanent link to this revision, which may differ significantly from the current revision.
Jet or Rocket engine Mass, kg Jet or rocket thrust, kN Thrust-to-weight ratio
RD-0410 nuclear rocket engine[1][2] 2000 35.2 1.8
J-58 (SR-71 Blackbird jet engine)[3][4] 2722 5.2
Concorde's Rolls-Royce/Snecma Olympus 593
turbojet with reheat[5][6] 		3175 169.2 5.4
RD-0750 rocket engine, three-propellant mode[7] 4621 1413 31.2
RD-0146 rocket engine[1] 260 98 38.5
Space Shuttle's SSME rocket engine[8] 3177 2278 73.2
RD-180 rocket engine[9] 5393 4152 78.6
F-1 (Saturn V first stage)[10] 8391 7740.5 94.1
NK-33 rocket engine[11] 1222 1638 136.8

Rocket thrusts are vaccuum thrusts unless otherwise noted

  1. ^ a b Wade, Mark. "RD-0410". Encyclopedia Astronautica. Retrieved 2009-09-25. Cite error: The named reference "astronautix1" was defined multiple times with different content (see the help page).
  2. ^ "«Konstruktorskoe Buro Khimavtomatiky» - Scientific-Research Complex / RD0410. Nuclear Rocket Engine. Advanced launch vehicles". KBKhA - Chemical Automatics Design Bureau. Retrieved 2009-09-25.
  3. ^ Aircraft: Lockheed SR-71A Blackbird
  4. ^ "Factsheets : Pratt & Whitney J58 Turbojet". National Museum of the United States Air Force. Retrieved 2010-04=-15. {{cite web}}: Check date values in: |accessdate= (help)
  5. ^ "ROLLS-ROYCE SNECMA OLYMPUS - Jane's Transport News". Retrieved 2009-09-25. With afterburner, reverser and nozzle ... 3,175 kg ... Afterburner ... 169.2 kN
  6. ^ [1]
  7. ^ "«Konstruktorskoe Buro Khimavtomatiky» - Scientific-Research Complex / RD0750". KBKhA - Chemical Automatics Design Bureau. Retrieved 2009-09-25.
  8. ^ SSME
  9. ^ "RD-180". Retrieved 2009-09-25.
  10. ^ http://www.astronautix.com/engines/f1.htm
  11. ^ Astronautix NK-33 entry
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