Hi Don,
I need to update my project page on the CD website - I've made a fair amount of progress since.
You can download a set of full scale plans from the website that will give you all the dimensions you are looking for. The plans are very detailed.
www.ihpa.ie/carbon-dragon/index.php/home...ans#full-scale-plans
For calculating wing and rib stress loadings, download my Excel spreadsheet and plug in your own figures for pilot weights etc. I highly recommend you get a copy of Jim Marske's Composite Design Manual, which contains all the methods and calculations I used in my spreadsheet. It will help you understand wing stress analysis.
www.ihpa.ie/carbon-dragon/index.php/cd-b...wing-stress-analysis
www.marskeaircraft.com/flying-wings.html - Composite Design Manual.
I can't help you with specific torque calculations as I didn't do any in my spreadsheet! I simply know that a leading edge made of two layers of carbon fiber (at +/-45deg to the long axis) are both stiffer and stronger than the original 0.8mm plywood leading edge specified in the original plans. Both Steve Arndt and Rick Mullins built their CDs using just two layers of carbon cloth and have load tested them to +5g and flown them at 70+mph without any issues. I plan to stiffen my leading edges even further using three layers (carbon-kevlar-carbon) to allow me to tow at even higher speeds behind a conventional sailplane tug. There will be a slight weight penalty but I have already managed to save significant weight in other areas (wing ribs and tail boom) so the net weight gain should be minimal if any.
My CD design has a wing loading of around 1.7lbs/sq-ft. Higher wing loadings will mean a higher sink rate.
All the best,
Phil.
This is a message from Don B at Carbon-Dragon (
www.ihpa.ie/carbon-dragon ) to you:
I see you are way into a modification of the CD. It looks like you know what you are doing, which is why I write. I personally do not work well with composites, and desire a CD that can live outside on the ramp. I am investigating a powered version with a giant scale model aircraft engine 15 hp 8 lb. My area does not have a glider launch near by (NJ near Phil). I am trying to design out of aluminum, but lack some basic data. Right now I am looking for airfoil data and trying to size the ribs and spacing. I am looking for the cord-wise air-load distribution. Or basically how much more that 2 lb/sq ft. should I figure the leading edge load, and what torque did you use.