Also... Howdy y’all! Its been a while since we checked in with you guys on the forum, so I want to give you a little update on what progress we’ve made recently. I also have a quick question for y’all that I’ll get to later.

In terms of progress, we are currently ready to construct our wing. We have done several rib tests and determined that our best bet is to use xps foam, but instead of doing wood rib caps as we had planned, to use e glass composite caps, which will increase both strength and ease of construction. We also had issues with our spar tearing through the foam, so we manufactured metal washers to go around the attachment hole and increase the foam’s tearout strength. All of the materials needed to manufacture our wing have arrived, so all that’s left to do is check our numbers and roll.

That’s where you guys come in and the question I have - we were doing some number checks, which led us down a rabbit hole of stall lift coefficient / velocities. We were looking over the Legal Eagle’s specs and comparing them to our own, and something didn’t seem right: their stall/max lift coefficient would need to be 1.9! (givens: dry weight = 246 lbs [plus pilot and whatever else we estimate to be similar to our own craft at around 508 lbs], stall velocity = 27 mph, wing area = 120 sq ft, and air density = 0.0765 lb/ft^3 [based on our own calculations]) Combine that with the standard equation for lift coefficient and you get around 1.64! If you run the same numbers for our current model (508 lbs weight, stall velocity = 24 kts, wing area = 186 sq ft, and air density = 0.0765 lb/ft^3) you get stall lift coefficient = 1.386, which is just under the max for the Clark Y, so that’s all good. (feel free to either trust us on that math or check it yourself, up to you, note: we arent 100% sure those numbers are correct but we are confident, also our numbers check our with this EAA provided ‘calculate your stall speed advisory,’ but theirs doesn’t [see page 21 of attached pdf]) Our one confusion is how does the Legal Eagle get away with that 1.64 lift coefficient? It doesn’t seem like their airfoil has that high of a max CL, so are we missing something? We are totally fine with using our current 186 sq ft wingspan as is, but ideally we can drop it down to somewhere near their 120, as it would save a large amount of weight. Our other specs are right on par with theirs, so can you guys see a reason why they can get away with a 1.64 CL and therefore a 120 sq ft wing? Thanks so much for all you help.