I do want to be cautious, I can make the front of my fuselage cross section round in order to eliminate the full length strake (ogee) going to the nose (SR-71 style), I can also eliminate the 'double' part of the delta, but would rather just make it smaller. I also wanted to avoid rolling up the aluminum by using a diamond shaped cross section all the way to the nose. I've been wondering about how this vortex unpredictability affects stability more than lift but lift enters into it too at landing speeds. I read somewhere, either on this thread or on the internet, that the double delta is the first planform of the delta styles to suffer from vortex breakdown. So the question is what happens to the stability when the vortex breaks down on a double delta? The two possible scenarios that I can think of are: 1.The vortex makes the main (rear delta) part of the wing produce lift so when the vortex is lost then it makes the craft pitch nose up. Or 2. When the vortex breaks down it causes the front, which is harder working to lose lift also. When the vortex goes away then the wing is stalled and then the stability is dominated by the area and center of area which would drop the nose. Similar to the results you would get with the 'cardboard cutout' method that can be used for initial determination of vertical tail volume, which would drop the nose.