I have two more questions (I'm pretty sure I can't find an answer to these anywhere else and you guys know your stuff).
1.) What is the thickness of the F-15's wings at the thickest point and/or the unexposed root [/i](where it's at 6.6%)[/i], the exposed root, and around the area where the wing reaches 3% T/C?
2.) What is the chordwise length of the F-15's wings at the thickest point and/or the unexposed root (where it's at 6.6%), the exposed root and around the area where the wing reaches 3% T/C?
Also, if anybody knows these ones... (I'm not even sure you guys will know this one, but I might as well ask)
1.) What is the T/C ratio of the F-15U's (The F-15E derivative with the enlarged wings) wings?
2.) Does anybody know the chordwise thickness of the F-15U's wings at the exposed root, the unexposed root (if possible), and at the tips?
3.) Does anybody know the chordwise length of the F-15U's wings at the exposed root, at the unexposed root (if possible), and at the tips?
Kendra Lesnick
BTW: I have a good reason for why I'm asking all these extra questions... I'm actually working on a WHIF-design that is essentially an F-14/F-15 hybrid -- an "Eagle-ization of the F-14" if you will: The airplane basically is to look like a twin-seat F-15 style-design with the F-14's radome-size, the F-15U's larger wing area, the F-15A/C's wing-thickness, with droops and multiple-position flaps. Other ideas included a single all-moving vertical fin.
(I'm not trying to go off topic here... I just want people to know why I'm asking all these highly-detailed questions about the F-15 and it's wings!)