# Supersonic Fuselage design [closed]

What should be the ratio of the fuselage and wings in a maximum dimension limited condition supersonic delta wing aircraft? Also can anybody explain clearly the "supersonic area rule" or "Whitcomb area rule"? Is there anything else I need to take care of while designing a fuselage for supersonic conditions? Thanks.

• you could start by taking some lessons in aerodynamics and fluid dynamics. Jun 16, 2014 at 12:27
• Way above my pay grade, but a short answer is that if you plot the length of the aircraft on the x-axis and its cross sectional area on the y-axis, you want that curve to be as smooth as possible. If it isn't, you're going to have a large drag rise during transonic flight. So, if, say, as was true with the first F-102, you got a sudden increase in cross sectional area at the point of the fuselage and wing juncture, you could fix it (and they did) by narrowing the fuselage at the point to produce the now familiar "coke bottle" shape, which avoided that large drag rise. Jun 16, 2014 at 13:39
• Gaurang, you seriously cannot expect to rock up to some internet forum and find out everything you need to know to design supersonic planes. Very probably, nobody here has that kind of knowledge. Even if they did, it's the sort of thing you'd need to write a whole book to explain, if not a series of books. Nobody is going to invest that kind of time. Jun 16, 2014 at 15:39
• @DavidRicherby Also, this is not a forum. Jun 16, 2014 at 15:40
• A continuation of my previous comment: As I remember it, the area rule was necessary in an era of engines with insufficient power to overcome the transonic drag rise without it and then push aircraft through the transonic range. It's not necessary and not used today with our much more powerful engines. Jun 16, 2014 at 16:12