Sam, Sure, you can attach that paragraph to the folder. David J. Gall

Thanks for that, Jay! I've edited my earlier statement; now that I've seen the Waddelow canard plans and layup schedule I think it is well-engineered and appears to be adequately and conservatively de

Make them adjustable fore/aft like sailplanes do:

Regarding the Weishaar-Doyle LS-1 canard I can only say that they were successful. They designed it as a taildragger canard and only converted to tri-gear when they had directional control difficultie

Cool photo. Were you "1000 ft above" that layer?

Jay, Understood. That’s why I never release software tools that aren’t “ready for prime time.” LOL BTW, “relative column” nomenclature is an Option (Preference) setting in Excel that saves with the do

Jay, Understood – I was referring to its ancestral beginnings. Did you originally build it using defined names? If so, someone went to a lot of work to strip them out. <shrug> David J. Gall

I always thought it was just 6 lbs./gal, not 6.1. Is this "inflation"? LOL

Jay, Please use defined names and named ranges when building your spreadsheets and formulas. It is soooo much easier to follow a spreadsheet formula that reads “=MainTankUseableFuel+1” than it is to f

How much?

And then some *old* guy asks, “how much?” 😂

QPC 14.

Not stupid at all. That’s almost exactly what John Roncz did in designing the Long-EZ replacement canard airfoil, except he gave it a little “kick” up right at the trailing edge that helps “push” the

“If you’re flying without sparrow strainers (or their aerodynamic equivalent) you’re doing it wrong.” “I think Chris and David’s responses about the sparrow strainers suggests that that they believe y

Robert, You’re asking for a Masters’ level dissertation on pitch stability and control, all of which has been hashed over numerous times on these pages. Please read the archives. Long story short: fol

Jay, A drop test and a static load test are two different tests performed for two different reasons. An equivalence between a tip loading and a distributed loading is a theoretical calculation; the pu

Such a test as taxiing around in the rough is a wholly inadequate and uncontrolled test for any purpose other than showing that your Q doubles as an ATV. Also, to correlate deflection with g loading p

Or carve it from some 6 lb. urethane insulation foam similar to the 2 lb. urethane the original Q1 kit used — 6 lb. to better match the existing PU foam of the factory shell. Or take a section from a

Robert, That patch of glass you showed that’s “not wetted out enough with dry spots” looks like the original inside layer of the factory fuselage shells. The factory shells were (apparently) not made

Paul, You’re thinking of the Q2 wing. The Q1 wing shear web ends at BL52. See plans page 9-6: https://davidjgall.com/Q/Quickie/Quickie%20Plans/Quickie%20plans%20section%2009.pdf. David J. Gall