Enicalyth, thanks for the reply, and apologies for being so slow myself.
I “did the math” for the 340-500 and came up with CL of .525 (very close to your value of .522), 19.45 for L/D (again, very close to your 19.55 value) and 20.4 nm per 1000 lb at 780,000 lb (vice your 20.5).
Reference your “last word on the 777”, after 2 pages of calculations, I managed to generate your figures (only needed one piece of info you didn’t include; density at 33,000 ft). Not sure if I could do it in the cockpit though.
What still puzzles me is your explanation (in 2 different posts) of the use of total wetted area in the determination cdtot. First, if we consider D=.5 rho V squared S Cdtot where S is wing area, then this seems to determine Cdtot. Yet your quote
“Cdtot is the sum of all wetted areas plus fiddle factor time finishing coefficient...”
seems to be re defining cdtot.
Second, to
“then divide by wing area to get cdo”
again seems to be a paradox since cdo is already defined by cdtot=cdo + cdi + cdcc.
Can you help please?
Hawk