Hi,
I'm working on wave drag prediction and I'd really appreciate some help in understanding the numerical analysis of the supersonic area rule.
Many of the traditional papers on numerically analysing this rule did not have access to modern CAD software through which to measure cross-sectional areas at different Mach planes, and so used complex integrals and restrictions to define an aircraft using x,y,z points. I however can measure these areas easily and exactly, and so for each Mach cone can create a plot of cross-sectional area vs 'x' (length of aircraft).
The problem is, these are individual points measured and so not a constant function; by necessity they are joined by a straight line. Most numerical analyses require a defined function of the line by which to analyse the drag integral using the second derivative (see attached image). But with individual points joined by straight lines, the first derivative is constant, and the second is zero, so can the drag integral be analysed?
Any insight would be incredibly helpful. I'm sure I'm missing something as others must have analysed the drag using area measurements.
Thanks
Ed