Talk:V/STOL

Requested move

 * The following discussion is an archived discussion of a requested move. Please do not modify it. Subsequent comments should be made in a new section on the talk page. No further edits should be made to this section. 

The result of the move request was: page moved. Anthony Appleyard (talk) 16:23, 17 February 2010 (UTC)

Vertical/Short Takeoff and Landing → V/STOL — These all use acronyms: CTOL, STOL, STOVL, VTOL, VTOHL, CATOBAR, STOBAR, JATO/RATO. Though I dislike this, for the sake of commonality it should be moved. — username 1 (talk) 20:04, 9 February 2010 (UTC)
 * Support the current article name is inconsistent with the article. 70.29.210.242 (talk) 05:11, 10 February 2010 (UTC)
 * The above discussion is preserved as an archive of a requested move. Please do not modify it. Subsequent comments should be made in a new section on this talk page. No further edits should be made to this section.

Glossed over issue
I came here for information. Why do lift fans require greater than one power to weight ratio whereas Helicopters (aircraft because they use a rotating wing, the wing/rotor providing lift as the wing moves several hundred mph thru the air) and airplanes can fly with .16 power to weight ratio? TaylorLeem (talk) 04:18, 28 August 2020 (UTC)


 * may be able to answer this. BilCat (talk) 04:21, 28 August 2020 (UTC)


 * It's an apples-and-oranges comparison of units. Helicopters need to put out as much thrust as they have weight to get off the ground, but you can't measure thrust in hp, which is typically how helicopter engine output is reported, while VTOL aircraft thrust is reported in lbs or kg. Helicopters use their engines to turn a rotor which is large in diameter and accelerates a large amount of air downwards. It's much more efficient to hover like that than by accelerating a small amount of air at high speed, but they all require as much thrust as they have weight. - Ahunt (talk) 12:59, 28 August 2020 (UTC)