Summary

Source is OpenDocument spreadsheet LiftThrust.ods at http://www.mediafire.com/download.php?zymmzm1xdlj (also by this author, in public domain), please beautify and/or convert to .SVG (scalable) format
Aircraft thrust and lift forces induced by engines (not wing lift), in a scenario of nearly zero altitude and airspeed
Some aircraft have different thrust in different airspeeds
(table is easier to read in edit)
Force (kN) notes
Aircraft Mode Thrust Lift Links to references
F-35B Horizontal 111 0 1 http://www.jsf.mil/downloads/mediakits/7764.zip archive copy at the Wayback Machine
Vertical 0 175 http://www.f135engine.com/proven-tech/engine_chacter.shtml archive copy at the Wayback Machine
STOVL 70 105 2 http://www.f135engine.com/proven-tech/engine_chacter.shtml archive copy at the Wayback Machine
Afterburner 178 0 1 http://www.jsf.mil/downloads/mediakits/7764.zip archive copy at the Wayback Machine
V-22 Horizontal 253 0 7 http://www.flightglobal.com/blogs/the-dewline/2009/06/boeing-looks-ahead-to-a-v-23-o.html
Vertical 0 230 2; 3 http://www.navair.navy.mil/v22/?fuseaction=aircraft.main archive copy at the Wayback Machine
AV-8B Harrier II
Horizontal 65 0 1; 6 http://www.airforce-technology.com/projects/harrier/specs.html
Vertical 0 86 2; 4 http://www.history.navy.mil/planes/av-8b.pdf
F16 Dry thrust 79 0 1 http://www.aerospaceweb.org/aircraft/fighter/f16/
XV-5 Horizontal 23 0 5 http://www.globalsecurity.org/military/systems/aircraft/xv-5-specs.htm
Vertical 0 71 source unverifyable http://www.aero-web.org/specs/ryan/xv-5a.htm

Notes:
1 Near, but not zero airspeed/altitude (unfeasible in this position)
2 Thrust is vectorable between 0 and 90 degrees, more in most aircrafts. Only tail thrust is vectorable in F-35B
3 Actually higher than this; estimated from max. Vertical takeoff weight times gravity constant : 23,495kg*9.81m/s = 230kN
4 Normal lift dry: 100%RPM for 2.5minutes including splay loss, up to 95.86kN available
5 Unknown variation between horizontal and vertical
6 Maximum continous. Details not available for AV-8B-Plus-version with Pegasus 11-61/Mk.107 at 106kN
7 Boeing estimates 10% ”download” (downwash loss) in vertical mode, meaning that horizontal thrust is 10% bigger than vertical
TGCP (talk) 20:30, 18 April 2010 (UTC)

Licensing

I, the copyright holder of this work, release this work into the public domain. This applies worldwide. In some countries this may not be legally possible; if so: I grant anyone the right to use this work for any purpose, without any conditions, unless such conditions are required by law.