Sorry guys, I'm not getting very much done at the moment, the new job I started isn't quite what I was told it would be. I was told it would be 4 days on, 4 days off, but I've only had one day off in two weeks working 12 hr shifts (plus 3 hrs traveling) and tomorrow I start night shift for a week.
I have managed to transfer the wing chord profiles into my computer and started to work out the parts I need for the multiple spars for the wing/fuselage connection. I've discovered something else though, what I have found by looking at cutaway drawings of the Vulcan, that aircraft's main and rear fuselage is in line with the wing chord center with the nose section drooping down 4.5 degrees. This doesn't happen with the Atlantic -- so now I have to decide which is the easiest way to create my new connecting spars. Do I keep them vertical to the fuselage, or vertical to the chord centerline. This is because the Vulcan wing has an incidence of 4.5 degrees although the most I can get with the Atlantic is 3.5 degrees. This is mainly to do with where the RW spars would be in the wing in relation to where the cabin floor is in the Atlantic.
In this image below, you can see how the inner most chord profile (in purple) interacts with the Atlantic fuselage (in red). You can see one of the little stars right on the centerline of the fuselage, this happens to be about where the engine front is located which also has a short spar in a Vulcan wing, the main front Vulcan wing spar is further forward but in this project it doesn't have to be the front main spar ('cause there's no bomb bay in the Atlantic)
The two blue lines are where the fuselage starts to taper to the rear, #1 line is where the top profile line starts (also where the side profile lines start in the top view, also where the trailing edge of the wing is located), and #2 line is where the bottom profile line starts. I had thought this was to have more clearance when the aircraft rotates for take-off, but then realized it's nothing of the sort. This is because the tailpipe fairings hang way down below the bottom of the wing and would actually be the first thing that strikes the ground if the aircraft was over rotated. What I did find is that this bottom profile almost matches the rear third of the bottom chord profile of the wing,
So you can see the dilemma I have, do I make the new spars vertical to the fuselage (just need a round hole in some styrene and then work out the tapering of the wing from one mating surface to the other, or do I rotate these spars to make the tapering easier and then have to work out what the elliptical shape would be for the fuselage connection.
I should mention that the centerline of the chord I'm using, is actually the Vulcan kit's top and bottom wing half joint line and may not be the actual chord centerline, I mention this because when transferring the chord profiles into the computer, I found the bottom half of the chord is deeper than the top half, which would make the airfoil upside-down. Unless delta wings are like that ---
