Are you drawing your airfoil templates from coordinates or just tracing the scanned documents? I’ve encountered so much distortion from scans that I’ve taken to recreating the drawings from raw data.

Corbin, NEVERMIND. I guess I hit “send” too soon; I just found them in a subfolder I didn’t know I had. <shrug>

Corbin, if you’d be willing to share your scans it would save me some time. I intend to redraw mine in CAD before I build anything from them….

Good question. I have mine but I’m guarding them jealously. What do you need?

Mike, why are you looking at the main wing here? It’s the canard that controls liftoff speed….

Since we’re only interested in “ground angle of attack” the analysis centers on the canard with “flap extended” (full aft stick). Set the “ground angle of attack” via the tailspring installed angle/le

TAZ, Do the Jim-Bob six-pack (all six), do the alignment, and don't worry about the "ground angle of attack." That was a Gene Sheehan red herring that never made any sense except to deflect customer c

“The badge manager and I had a discussion. He believes that all pilots flying have some sort of training and badges that allow them to walk on the ramp.” Your badge manager CLEARLY failed the TSA trai

Eugen, 1) Keep the level lines parallel. 2) Keep the template trailing edges flush with a line parallel to the trimmed edge of the foam block. 3) Keep the level lines at the same height above the tabl

Eugen, I think you still do not have the centersection block correct. It’s hard to tell from SolidWorks screen shots without perspective turned on. In front view the block should be a trapezoidal shap

Eugen, Additional to my last note, see page 10-5. The aft “elevator slot cores” are also removed along the line 33-F-G-H-I-32 for the remainder of the canard beyond the center section, but only AFTER

Eugen, Read the plans as though the following image is a single page. The first paragraph shown here refers to the LAST drawing shown here and a drawing not shown here that is at the bottom of page 5-

Ha-ha! Touche! Yes, of course you are right. Not owning a -18°C freezer, I was thinking of room temperature cure low-vacuum consolidation to achieve ~50% resin content, not prepreg…. I can’t wait to s

Flax is inferior to highly-crystalline cellulose fiber for exactly the reasons mentioned below. Highly-crystalline cellulose fiber is nearly equivalent to E-glass in all respects except weight -- glas

https://davidjgall.com/Q/LS(1)%20canard/

Rob, Fuselage torsional stiffness is low until the wing and canard are installed. Eugen, Be sure to download the entire SuperQuickie Conversion report, not just the one picture that I sent earlier. ht

Vern, I appreciate your enthusiasm but: Carbon and titanium and prohibitions – oh, my! These planes are made from super-cheap insulation materials sourced from Home Depot and a second-hand generator m

Eugen, Yes, you understand the plans correctly with regard to the BID. You really should have a PDF of the original plans for reference; the OCR version on the Quickheads site is very well done but so

“I did not catch up that point yet.” I’m not sure I understand your reply. To clarify my point: plans page 4-3 comes before plans chapter 7 so glassing the firewall should have been completed before f

Eugen, aren’t you supposed to have 1 ply BID on each side of the firewall before fuselage assembly? See plans page 4-3.