Larry, Thrust is destabilizing. Camber change due to canard "bowing" under aerodynamic lift at 1 gee is approximately 40% of camber change due to canard bowing due to airplane weight fully supported b

Bob, Respectfully, I disagree. It may also be adverse yaw, but it is also something more than just adverse yaw. David J. Gall

I don't think reverse aileron steering is eliminated by setting positive camber. You still have the same flexible canard causing a difference in camber between the left and right wheels when a moment

Nicely said. You could extend this to explain "reverse aileron steering," too. David J. Gall

Doug, Jeff, Never mind asking Velocity Aircraft about these parts. Contact Scott Swing directly (through Velocity). Tri-Q parts were never part of the "Velocity business" and I'd bet that they did not

General, Your best bet is to buy Leon McAtee's redrawn CAD templates for the Q1 LS(1) canard. David J. Gall

Dan, Your second link is incorrect. The correct link is: http://www.nasg.com/afdb/show-airfoil-e.phtml?id=832 David J. Gall

LS canard: NASA LS(1)-0417MOD GU canard: Glasgow University GU25-5(11)8 Main Wing: Possibly Eppler 1230MOD, unconfirmed. IF you find airfoil performance information for any of the above, PLEASE share!

That's exactly what the Q200 is and was designed to do....

Tad, You obviously did not build your Phoenix, otherwise you would not be prefacing "I believe" in front of your pronouncements about your canard's structural material. Please take the prudent/conserv

Thanks for the update, Peter. Isn't Oz in the Conclusion Islands chain? I've jumped there so many times I think I'm starting to know the place.... Arrgh! :-) Thanks for making spars. Buy my CD and Leo

GJG- The Roncz R1145MS airfoil is not a modified LS(1)-0417 airfoil. The LS(1)-0417 airfoil is 17% thick, the Roncz R1145MS is 20.5% thick and the GU25(5)11-8 airfoil is 21% thick. Part of the beauty

re: "Sammy Super Slippery Shroud" Try "spats" as in "Sammy's Super Slippery Spats"... :-)

Paul, My ACAD 14 wouldn't open the file: Unknown value "AC1015" encountered in drawing version. Error 4 in drawing header on line 8. Invalid or incomplete DXF input -- drawing discarded. David J. Gall

Bill, One can't add flaps to a Q2, the Q2 already has flaps. They're on the front wing. We just call 'em the "elevator" and use them more frequently than regular airplanes use theirs. That, and we cal

Gordon, BellSouth lost much of their newer switching equipment for the 407 and 772 area codes in the hurricanes last year and are still rebuilding the network in that area. The existing network is old

Dave, Check the last few pages of "superq.pdf" in the files area on the Q-LIST Yahoo Group. There's info there on the props used for the Rotax 503 conversion, and you can figure out the prop clearance

Try abebooks.com: http://dogbert.abebooks.com/servlet/SearchResults?imagefield.x=0&an=hoerner&tn=fluid+dynamic&imagefield.y=0 ...Or eBay.... David J. Gall

Sam, Also, take a look at http://naca.larc.nasa.gov/reports/1936/naca-report-540/. David J. Gall

Sam, Without surveying the literature: According to Hoerner's "Fluid Dynamic Drag" page 8-12, there's a chart that appears to show best drag reduction for fillet radii between 4% and 8% of the chord.