bronkk
Active Member
Well I finally am serious enough to post an actual analysis of my design (the "Warlock"). It's only the spar though. I have attached a drawing of the construction, a picture of the FEA analysis of stress results and a simplified lay up explanation pic. I also posted a material data table from an old EAA article with the Fiberglass layup data I used. One assumption I am making is that the .025" thick 3" wide unidirectional tape that aircraft spruce sells and I am planning on making the spar caps from has similar or the same properties as the .007" thick Rutan aircraft cloth.
I am designing my plane to be a 26 foot wingspan, 1320 LBS, and LSA compliant. I wish to design around the Utility Category design loads. My intention is to use a NACA 6614 airfoil. I am interested in comments on the spar attach, how I am continuing the side layups around the cap material and anything else I might be doing right or wrong...
You may note that its parallelogram shaped. This is so it follows the airfoil curve at 25% of chord. Also the analysis only included the lifting load not the induced moment or drag forces. I plan on doing a more complete analysis of the entire wing structure in the following few days. I am using Pro-Engineer's FEA (Mechanica) to perform the analysis. It actually has an easy to use shell feature to create layups. :whistle:
Kelly
It seems that perfection is attained not when there is nothing more to add, but when there is nothing more to remove.-Antoine de Saint Exupéry
I am designing my plane to be a 26 foot wingspan, 1320 LBS, and LSA compliant. I wish to design around the Utility Category design loads. My intention is to use a NACA 6614 airfoil. I am interested in comments on the spar attach, how I am continuing the side layups around the cap material and anything else I might be doing right or wrong...
You may note that its parallelogram shaped. This is so it follows the airfoil curve at 25% of chord. Also the analysis only included the lifting load not the induced moment or drag forces. I plan on doing a more complete analysis of the entire wing structure in the following few days. I am using Pro-Engineer's FEA (Mechanica) to perform the analysis. It actually has an easy to use shell feature to create layups. :whistle:
Kelly
It seems that perfection is attained not when there is nothing more to add, but when there is nothing more to remove.-Antoine de Saint Exupéry
