Jay, John Roncz came up with the solution to this many years ago. It’s called the “Roncz canard” in the Long-EZ community. It’s an excellent airfoil, but particularly important is what he did to the e

Sam, Yes, I have the Weishaar-Doyle plans. I’m working on redrawing the drawing because I can’t get a good copy without distortion. So I’m redrawing it in CAD.... David J. Gall

I can't see any photo or attachment with this post...?

Why not just dig up a copy of the old Weishaar & Doyle built-up carbon spar canard plans and start building?

Corbin, I worry for your safety. You seem much too cavalier in your approach to this task. Please let an experienced Q driver do your taxi testing and initial test flights. At the least, wear a helmet

Nice! Thanks for that.

Lapo, 1. There are no "design rights" but there is a copyright on the plans. There doesn't seem to be any interest in enforcing that copyright, however, as PDF copies are abundantly available. Good lu

Another good resource for used books is ABEBooks.com: https://www.abebooks.com/servlet/SearchResults?sts=t&cm_sp=SearchF-_-home-_-Results&an=Hoerner&tn=&kn=Fluid+dynamic&isbn=

Jay, Pitching moment does not increase with angle of attack. Please review NACA Report No. 824 or Theory of Wing Sections. You’ll find that the coefficient of moment is nearly constant across all non-

Jay, something doesn’t add up. At constant gross weight and CG location, you cite liftoff at two different combinations of elevator and reflexor deflection that seem incompatible to me. In one, your r

Matt, The workmanship looks good. However: The design of the area between the bottom of the cheeks and the top of the canard is a big aerodynamic boo-boo. The interference drag will cost you big mph o

I think you're in way over your head.

Matthew, 1° toe out is not "slight" but "moderate." With tires, think in terms of an aerodynamic surface deflection, then divide by three. So 1° toe out would be like 3° rudder deflection. You want to

Matthew, The "Gall alignment" is only part of the equation. It isn't complete until you do the "Jim-Bob six-pack," too. Please do the independent toe brakes, etc. ASAP. Jim Patillo can fill you in on

Jimmeh, I don't know what killed Marc Waddellow either, but I can surmise based on these excerpts from the Halon 1301 MSDS and the circumstances of his death in his basement that Halon exposure may ha

All respect and kudos to Mr. Seguin, however, trying to expand the envelope to crosswind landings (15 to 18 kts direct x-wind) on flight number three with 0.8 hours on the airplane is ... well ... dum

In other words, the experiment has already been conducted and it was a failure resulting in the death of the experimenter. End of discussion ... please?

Brad, Normally I would concur, except in the specific case of glueing multiple sheets to obtain the block thickness needed for wing/canard cores, it apparently has been tried with fatal results. So ha

Uzair, The bulkhead and console foam ("white foam") is approximately 5/16" or 3/8" or 6mm thick depending on how closely you want to measure. :) As I posted earlier, it is General Plastics Last-a-Foam

Uzair, The urethane foam for the fuselage is NOT Divinycell foam, it is cheap urethane "T2000" insulation contractor foam, again, available locally to anyone near a medium sized metropolitan area. Ask