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|archive = Talk:SpaceX reusable launch system development program/Archive 1
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== First stage velocity at separation ==
It is probably time to revisit the article info on separation speeds before booster flyback. New, specific, info is available on the first two actual flights of the [[Falcon 9 full thrust]] version of the rocket is now available: [[Falcon 9 Flight 20]] in Dec 2015 and [[Falcon 9 Flight 22]], slated for launch later today. This source (<!-- <ref name=reuters20160223> -->
{{cite news |last=Klotz |first=Irene |url=http://www.reuters.com/article/us-space-spacex-ses-idUSKCN0VW2O7 |title=Satellite operator SES says interested in used SpaceX rocket |work=Reuters |date=2016-02-23 |accessdate=2016-02-24 }}<!-- </ref> -->) provides clear info on the Falcon 9 part of the question:
<blockquote>the rocket launching this week will be flying almost twice as fast as the one used in December - between 4,971- to 5,592 mph ( 8,000- to 9,000 kph), compared to 3,107 mph (5,000 kph) - by the time it separates from the second-stage motor, SpaceX said. </blockquote>
FWIW, the info on these velocities that is currently in the first paragraph of this article, is based on orginal forward-looking design information from several years ago in 2012 (and there was lengthy Talk page discussion getting to that...):
<blockquote> If the technology is used on a reusable Falcon 9 rocket, the first-stage separation would occur at a velocity of approximately 2.0 km/s (6,500 km/h; 4,100 mph; Mach 6) rather than the 3.4 km/s (11,000 km/h; 7,000 mph; Mach 10) for an expendable Falcon 9, to provide the residual fuel necessary for the deceleration and turnaround maneuver and the controlled descent and landing.</blockquote>
So the article will definitely need an update, and I don't have time to do it just now. [[User:N2e|N2e]] ([[User talk:N2e|talk]]) 12:57, 24 February 2016 (UTC)
== Flight 22 landing: Significance of extra push - consequently phrasing looks wrong ==
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