Originally Posted by
Central Scrutinizer
Well then the limitation becomes the Vmo. Assuming Vmo is a fixed number independent of mass, both aircraft descend at the same IAS, the heavier one should have a higher L/D ratio (more lift for the same amount of drag) and therefore a shallower descent angle (more track miles).
Vmo is independent of weight. Buffet boundaries however are not, so may affect manoeuvre margins.
Have a look at this chart, and then perhaps consider your statement. You are around 90% there, but that means a 100% review.
Consider first level flight at a constant AOA; total lift variables for a comparison are Lift =CL.V^2, that's the set of variables. everything else is lipgloss in a comparative analysis. So, as Lift must equal weight for level flight, the heavier aircraft must either have a higher CL for a constant speed, or an increased speed for a constant CL. CL is related to the a-slope of CL v AOA. In general the relationship of almost all systems will be around 0.09 CL for every degree of AOA. There are a few things that will affect that, such as aspect ratio, and very slightly VGs can increase that slope... trailing edge mods may also increase that slope.
So, thinking laterally from that case, consider when the aircraft is in a straight glide.. the chart will get you to your journey.
May the forces be with you
