Editing RL10 (section)

==Partial specifications==
===All versions===
* Contractor: Pratt & Whitney
* Propellants: liquid oxygen, liquid hydrogen<ref name="pwr_rl10b-2.pdf" />
* Design: [[expander cycle]]<ref name="Sutton1998">{{Cite journal |last1=Sutton |first1=A. M. |last2=Peery |first2=S. D. |last3=Minick |first3=A. B. |date=January 1998 |title=50K expander cycle engine demonstration |url=https://apps.dtic.mil/sti/pdfs/ADA397948.pdf |url-status=live |journal=AIP Conference Proceedings |volume=420 |pages=1062–1065 |bibcode=1998AIPC..420.1062S |doi=10.1063/1.54719 |archive-url=https://web.archive.org/web/20130408132823/http://www.dtic.mil/cgi-bin/GetTRDoc?AD=ADA397948 |archive-date=April 8, 2013}}</ref>
* Ignition: electric spark.<ref>{{cite web |last1=McCutcheon |first1=Kimble D. |title=U.S. Manned Rocket Propulsion Evolution, Part 8.21: The Pratt & Whitney RL10 Engine |url=https://enginehistory.org/Rockets/RPE08.21/RPE08.21.shtml |website=Aircraft Engine Historical Society |access-date=28 August 2024}}</ref>

=== RL10A ===
[[File:RL-10 rocket engine.jpg|thumb|300px|RL10A information and overview]]
* Thrust (altitude): 15,000{{nbsp}}[[pound-force|lb-f]] (66.7&nbsp;kN)<ref name="S2S">{{Cite book |last=Bilstein |first=Roger E. |url=https://history.nasa.gov/SP-4206/ch5.htm |title=Stages to Saturn; A Technological History of the Apollo/Saturn Launch Vehicles |date=1996 |publisher=NASA History Office |location=Washington, D.C. |chapter=Unconventional Cryogenics: RL-10 and J-2 |access-date=December 2, 2011}}</ref>
* [[Specific impulse]]: {{convert|433|isp}}
* Engine weight, [[dry weight|dry]]: 298&nbsp;lb (135&nbsp;kg)<!-- https://web.archive.org/web/20020826015127/http://www.astronautix.com/engines/rl10.htm says 288 lb/131 kg -->
* Height: 68{{nbsp}}in (1.73{{nbsp}}m)
* Diameter: 39{{nbsp}}in (0.99{{nbsp}}m)
* Nozzle expansion ratio: 40 to 1
* Propellant flow: 35&nbsp;lb/s (16&nbsp;kg/s)
* Vehicle application: [[Saturn I]], [[S-IV]] 2nd stage, 6 engines
* Vehicle application: [[Centaur (rocket stage)|Centaur]] upper stage, 2 engines

===RL10B-2===
[[File:Second stage of a Delta IV Medium rocket.jpg|thumb|Second stage of a Delta IV Medium rocket featuring an RL10B-2 engine]]
* Thrust (altitude): 24,750&nbsp;lbf (110.1&nbsp;kN)<ref name="pwr_rl10b-2.pdf">{{Cite web |date=2009 |title=RL10B-2 |url=http://www.pw.utc.com/products/pwr/assets/pwr_rl10b-2.pdf |url-status=dead |archive-url=https://web.archive.org/web/20120326211303/http://www.pw.utc.com/products/pwr/assets/pwr_rl10b-2.pdf |archive-date=March 26, 2012 |access-date=January 29, 2012 |publisher=[[Pratt & Whitney Rocketdyne]] |df=mdy-all}}</ref>
* [[Specific impulse]]: {{convert|465.5|isp|}}<ref name="pwr_rl10b-2.pdf" />
* Engine weight, dry: 664&nbsp;lb (301.2&nbsp;kg)<ref name="pwr_rl10b-2.pdf" />
* Height: 163.5{{nbsp}}in (4.14{{nbsp}}m)<ref name="pwr_rl10b-2.pdf" />
* Diameter: 84.5{{nbsp}}in (2.21{{nbsp}}m)<ref name="pwr_rl10b-2.pdf" />
* Expansion ratio: 280 to 1
* Mixture ratio: 5.88 to 1 oxygen:hydrogen mass ratio<ref name="pwr_rl10b-2.pdf" />
* Propellant flow: fuel, 7.72&nbsp;lb/s (3.5&nbsp;kg/s); oxidizer 45.42&nbsp;lb/s (20.6&nbsp;kg/s)<ref name="pwr_rl10b-2.pdf" />
* Vehicle application: [[Delta III]], Delta IV second stage (1 engine)