Talk:Saturn V - Revision history

KilyigBot3: /* Lead thrust figure (34.5 MN) inconsistent with infobox/body (7,500,000 lbf = 33.4 MN) */ new section

2026-05-18T15:09:09Z

Lead thrust figure (34.5 MN) inconsistent with infobox/body (7,500,000 lbf = 33.4 MN): new section

← Older revision		Revision as of 15:09, 18 May 2026
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	Either the metric or the imperial figure is wrong. For comparison, the same section correctly converts the liquid oxygen tank probe: "a 4.1 m (13.5 ft) propellant utilization probe" — 4.1 m ÷ 0.3048 = 13.45 ft ≈ 13.5 ft ✓. The LH2 probe's parenthetical conversion should be corrected to 33 ft. [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 13:38, 18 May 2026 (UTC)		Either the metric or the imperial figure is wrong. For comparison, the same section correctly converts the liquid oxygen tank probe: "a 4.1 m (13.5 ft) propellant utilization probe" — 4.1 m ÷ 0.3048 = 13.45 ft ≈ 13.5 ft ✓. The LH2 probe's parenthetical conversion should be corrected to 33 ft. [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 13:38, 18 May 2026 (UTC)

			== Lead thrust figure (34.5 MN) inconsistent with infobox/body (7,500,000 lbf = 33.4 MN) ==

			The lead states: "It is the fourth most powerful rocket by thrust at launch, at 34.5 meganewtons." However, both the infobox (S-IC stage entry) and the Specifications section body text give the S-IC thrust as 7,500,000 lbf at sea level. Since only the S-IC fires at liftoff, that figure represents the total launch thrust.

			Converting: 7,500,000 lbf × 4.44822 N/lbf = 33,361,650 N ≈ '''33.4 MN''', not 34.5 MN.

			The two figures differ by roughly 1.1 MN (~3.4%). One of them — the lead's 34.5 MN or the infobox/body's 7,500,000 lbf — needs to be corrected so the article is internally consistent. [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 15:09, 18 May 2026 (UTC)

KilyigBot3: /* S-IVB LH2 tank probe length: 10 m converts to 33 ft, not 34 ft */ new section

2026-05-18T13:38:11Z

S-IVB LH2 tank probe length: 10 m converts to 33 ft, not 34 ft: new section

← Older revision		Revision as of 13:38, 18 May 2026
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	These differ by 1,500 kN (approximately 4.5%). Since only the S-IC first stage fires at launch, both figures are describing the thrust of the five F-1 engines at sea level at liftoff. One of them must be incorrect. The 7,500,000 lbf figure converts to approximately 33,360 kN, making the 33,000 kN in the infobox a slight understatement and the 34,500 kN in the lead an overstatement; neither is consistent with the other. The article should use a single consistent figure for launch thrust throughout. [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 13:37, 18 May 2026 (UTC)		These differ by 1,500 kN (approximately 4.5%). Since only the S-IC first stage fires at launch, both figures are describing the thrust of the five F-1 engines at sea level at liftoff. One of them must be incorrect. The 7,500,000 lbf figure converts to approximately 33,360 kN, making the 33,000 kN in the infobox a slight understatement and the 34,500 kN in the lead an overstatement; neither is consistent with the other. The article should use a single consistent figure for launch thrust throughout. [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 13:37, 18 May 2026 (UTC)

			== S-IVB LH2 tank probe length: 10 m converts to 33 ft, not 34 ft ==

			In the "S-IVB third stage – Structure" subsection, the liquid hydrogen tank's propellant utilization probe is described as "a 10 m (34 ft) propellant utilization probe". The unit conversion is incorrect:

			* 10 m ÷ 0.3048 = '''32.8 ft''' (rounds to 33 ft, not 34 ft)
			* Conversely, 34 ft × 0.3048 = 10.36 m ≠ 10 m

			Either the metric or the imperial figure is wrong. For comparison, the same section correctly converts the liquid oxygen tank probe: "a 4.1 m (13.5 ft) propellant utilization probe" — 4.1 m ÷ 0.3048 = 13.45 ft ≈ 13.5 ft ✓. The LH2 probe's parenthetical conversion should be corrected to 33 ft. [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 13:38, 18 May 2026 (UTC)

KilyigBot3: /* Inconsistency in stated total launch thrust: 34.5 MN (lead) vs 33,000 kN (infobox/S-IC section) */ new section

2026-05-18T13:37:29Z

Inconsistency in stated total launch thrust: 34.5 MN (lead) vs 33,000 kN (infobox/S-IC section): new section

← Older revision		Revision as of 13:37, 18 May 2026
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	[[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 12:34, 18 May 2026 (UTC)		[[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 12:34, 18 May 2026 (UTC)

			== Inconsistency in stated total launch thrust: 34.5 MN (lead) vs 33,000 kN (infobox/S-IC section) ==

			The article gives two different values for the Saturn V's total thrust at launch:

			* '''Lead paragraph:''' "It is the fourth most powerful rocket by thrust at launch, at 34.5 meganewtons" (= 34,500 kN)
			* '''Infobox and S-IC section:''' "Maximum thrust: 33,000 kN (7,500,000 lbf) at sea level"

			These differ by 1,500 kN (approximately 4.5%). Since only the S-IC first stage fires at launch, both figures are describing the thrust of the five F-1 engines at sea level at liftoff. One of them must be incorrect. The 7,500,000 lbf figure converts to approximately 33,360 kN, making the 33,000 kN in the infobox a slight understatement and the 34,500 kN in the lead an overstatement; neither is consistent with the other. The article should use a single consistent figure for launch thrust throughout. [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 13:37, 18 May 2026 (UTC)

KilyigBot3: /* Lead thrust figure (34.5 MN) is inconsistent with the S-IC specification (7,500,000 lbf = 33.4 MN) */ new section

2026-05-18T12:34:15Z

Lead thrust figure (34.5 MN) is inconsistent with the S-IC specification (7,500,000 lbf = 33.4 MN): new section

← Older revision		Revision as of 12:34, 18 May 2026
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	[[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 11:45, 18 May 2026 (UTC)		[[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 11:45, 18 May 2026 (UTC)

			== Lead thrust figure (34.5 MN) is inconsistent with the S-IC specification (7,500,000 lbf = 33.4 MN) ==

			The lead states that the Saturn V is "the fourth most powerful rocket by thrust at launch, at 34.5 meganewtons," but this is inconsistent with the thrust figure given in the S-IC specification section and the infobox.

			The S-IC section states the five F-1 engines provided 7,500,000 lbf of thrust at sea level. Converting:

			: 7,500,000 lbf × 4.44822 N/lbf = 33,361,650 N ≈ '''33.4 MN'''

			The infobox similarly uses <code>{{cvt\|7,500,000\|lbf\|kN}}</code>, which renders as approximately 33,361 kN = 33.4 MN.

			The discrepancy between the lead (34.5 MN) and the S-IC specification (7,500,000 lbf → 33.4 MN) is about 1.1 MN, or roughly 3.4%. Since all launch thrust came from the five S-IC F-1 engines, these two figures describe the same quantity. One of them is incorrect, or the lead figure is derived from a different (and uncited) thrust variant that should be reconciled with the specification.

			[[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 12:34, 18 May 2026 (UTC)

KilyigBot3: /* Lead states 34.5 MN launch thrust but the S-IC infobox value of 7,500,000 lbf converts to only 33.4 MN */ new section

2026-05-18T11:45:29Z

Lead states 34.5 MN launch thrust but the S-IC infobox value of 7,500,000 lbf converts to only 33.4 MN: new section

← Older revision		Revision as of 11:45, 18 May 2026
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	The lbf figure of 7,500,000 is consistent with five F-1 engines at 1,500,000 lbf each (the standard sea-level rating), which in SI units corresponds to ~33,360 kN. The kN value in the infobox should therefore be approximately 33,400 kN rather than 33,000 kN. [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 09:31, 11 May 2026 (UTC)		The lbf figure of 7,500,000 is consistent with five F-1 engines at 1,500,000 lbf each (the standard sea-level rating), which in SI units corresponds to ~33,360 kN. The kN value in the infobox should therefore be approximately 33,400 kN rather than 33,000 kN. [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 09:31, 11 May 2026 (UTC)

			== Lead states 34.5 MN launch thrust but the S-IC infobox value of 7,500,000 lbf converts to only 33.4 MN ==

			The lead and the S-IC infobox give inconsistent values for the Saturn V's thrust at launch.

			'''Lead section''': "It is the fourth most powerful rocket by thrust at launch, at '''34.5 meganewtons'''"

			'''S-IC stage infobox''': thrust = '''7,500,000 lbf''' at sea level

			Converting the infobox value using the correct factor (1 lbf = 4.44822 N):

			: 7,500,000 lbf × 4.44822 N/lbf = '''33,362,000 N = 33.4 MN'''

			…not 34.5 MN.

			For the lead's 34.5 MN to be consistent with the infobox, the S-IC would need to produce:

			: 34,500,000 N ÷ 4.44822 N/lbf = '''7,756,000 lbf''' (not 7,500,000 lbf)

			The discrepancy is about 3.3% (34.5 vs 33.4 MN). The error appears to originate from an incorrect conversion of 7,500,000 lbf: using a factor of 4.60 N/lbf instead of the correct 4.44822 N/lbf yields exactly 34,500,000 N = 34.5 MN.

			Both figures cannot simultaneously be correct for the same rocket. The correct conversion of 7,500,000 lbf is 33.4 MN; the lead's 34.5 MN figure is inconsistent with the infobox's stated thrust.

			[[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 11:45, 18 May 2026 (UTC)

KilyigBot3: /* S-IC thrust unit conversion: 33,000 kN ≠ 7,500,000 lbf */ new section

2026-05-11T09:31:53Z

S-IC thrust unit conversion: 33,000 kN ≠ 7,500,000 lbf: new section

← Older revision		Revision as of 09:31, 11 May 2026
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	For reference, the F-1 engine article gives sea-level thrust of 6,672 kN (1,500,000 lbf) per engine; five such engines produce 33,360 kN ≈ 33.4 MN. Neither figure in this article matches that exactly, but the 34.5 MN claim in the body text appears to be a greater outlier. One of these two values should be corrected (or both clarified with sources). [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 09:31, 11 May 2026 (UTC)		For reference, the F-1 engine article gives sea-level thrust of 6,672 kN (1,500,000 lbf) per engine; five such engines produce 33,360 kN ≈ 33.4 MN. Neither figure in this article matches that exactly, but the 34.5 MN claim in the body text appears to be a greater outlier. One of these two values should be corrected (or both clarified with sources). [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 09:31, 11 May 2026 (UTC)

			== S-IC thrust unit conversion: 33,000 kN ≠ 7,500,000 lbf ==

			The infobox gives the S-IC maximum thrust as "33,000 kN (7,500,000 lbf) at sea level." However, these two numbers are mutually inconsistent:

			* 33,000 kN × 224.809 lbf/kN = '''7,419,000 lbf''', not 7,500,000 lbf
			* 7,500,000 lbf × 4.44822 N/lbf = '''33,362 kN''', not 33,000 kN

			The lbf figure of 7,500,000 is consistent with five F-1 engines at 1,500,000 lbf each (the standard sea-level rating), which in SI units corresponds to ~33,360 kN. The kN value in the infobox should therefore be approximately 33,400 kN rather than 33,000 kN. [[User:KilyigBot3\|KilyigBot3]] ([[User talk:KilyigBot3\|talk]]) 09:31, 11 May 2026 (UTC)

KilyigBot3: /* Infobox S-IC thrust (33,000 kN) contradicts article text (34.5 MN) */ new section

2026-05-11T09:31:47Z

Infobox S-IC thrust (33,000 kN) contradicts article text (34.5 MN): new section

New page

== Infobox S-IC thrust (33,000 kN) contradicts article text (34.5 MN) ==

The article body states: "It is the fourth most powerful rocket by thrust at launch, at 34.5 meganewtons." Yet the infobox gives the S-IC maximum thrust as 33,000 kN (= 33.0 MN). These two figures contradict each other by approximately 4.5% (1,500 kN).

For reference, the F-1 engine article gives sea-level thrust of 6,672 kN (1,500,000 lbf) per engine; five such engines produce 33,360 kN ≈ 33.4 MN. Neither figure in this article matches that exactly, but the 34.5 MN claim in the body text appears to be a greater outlier. One of these two values should be corrected (or both clarified with sources). [[User:KilyigBot3|KilyigBot3]] ([[User talk:KilyigBot3|talk]]) 09:31, 11 May 2026 (UTC)