File:H-1 rocket engine diagram image.jpg

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Original file (439 × 623 pixels, file size: 40 KB, MIME type: image/jpeg)

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Summary

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Description
English: The H-1 rocket engine
&nbsp Vehicle Effectivity
SA-201 through SA-205 SA-206 and subsequent
Thrust (sea level) 200,000 lb (890 kN) 205,000 lb (912 kN)
Thrust duration 155 sec 155 sec
Specific impulse (lb-sec/lb) 260.5 min 261.0 min
Engine weight dry (inboard) 1,830 lb (830 kg) 2,200 lb (998 kg)
Engine weight dry (outboard) 2,100 lb (953 kg) 2,100 lb (953 kg)
Engine weight burnout 2,200 lb (998 kg) 2,200 lb (998 kg)
Exit-to-throat area ratio 8:1 8:1
Propellants LOX & RP-1 LOX & RP-1
Mixture ratio 2.23±2% 2.23±2%
  • Contractor: NAA/Rocketdyne
  • Vehicle application: Saturn IB/S-IB stage (eight engines)
Source derivative work of Image:H-1_rocket_engine_diagram.jpg from https://web.archive.org/web/20040219185137/http://mix.msfc.nasa.gov/IMAGES/MEDIUM/9801768.jpg
Author NASA
Other versions
The H-1 image came from this NASA graphic showing the specifications outlined in the table above.


Licensing

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Public domain This file is in the public domain in the United States because it was solely created by NASA. NASA copyright policy states that "NASA material is not protected by copyright unless noted". (See Template:PD-USGov, NASA copyright policy page or JPL Image Use Policy.)
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Original upload log

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Transferred from en.wikipedia to Commons using For the Common Good.

The original description page was here. All following user names refer to en.wikipedia.
Date/Time Dimensions User Comment
02:57, 9 July 2004 439 × 623 (40,744 bytes) w:en:Ke4roh (talk | contribs) (crop to just the engine)
01:27, 10 June 2004 640 × 480 (97,083 bytes) w:en:Reubenbarton (talk | contribs) (H-1 Saturn I and Saturn IB rocket engine)

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Date/TimeThumbnailDimensionsUserComment
current20:18, 20 August 2012Thumbnail for version as of 20:18, 20 August 2012439 × 623 (40 KB)Bulwersator (talk | contribs)Transferred from en.wikipedia: see original upload log above

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