Jon Meyer wrote:
I think you misunderstood what I meant.
The IAS VNE at cruising altitude of 20000ft is 272kts
(assuming as I said before that IAS VNE is at cruising
altitude) . This equates to a TAS of 364kts. Which
means that VNE is 364kts TAS.
So in this aircraft at sea-level you could technically
go to 364kts IAS and still be below VNE.

Did you really mean "Vne", or just flutter related aspects of Vne?
Obviously, the potential aerodynamic loads will be about 80% greater at
364kts TAS at sea level.

again I'll re-iterate that VNE is influenced by TAS
(and Mach Number) NOT by IAS, which is merely an approximation
of TAS valid at sea level.

But isn't aerodynamic pressure an important factor (i.e, "influence") in
flutter? And that is what IAS measures?
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Eric Greenwell
Washington State
USA