Jon,
My "calculation" of TAS being higher then VNE is flawed ???
It's simple. Real life scenario :
ASI has the VNE (painted on) at 255 kt.
Cruise IAS at 25000ft is 185Kt (well below the VNE).
OAT shows -25 celsius at this altitude.
The TAS calculation using any E6B computer shows TAS at this condition to be
272Kt.
I'll say again, TAS at this altitude is therefore 272kt.
If you were to reach VNE at this altitude, your TAS would be 364kt.
So you are IN FACT below VNE. Of course. That's the whole point.
The VNE painted on the ASI says 255Kt, but that is INDICATED, and someone
thought that was to be taken as TAS, which is wrong.
"Mark James Boyd" wrote in message
news:3fd75f4f$1@darkstar...
Jon Meyer wrote:
Sorry,
I am not confused about the issues concerning flutter.
Flutter is dependant on TAS. IAS is an arbitrary value
based on sea level air density. I still believe that
the reason you are confused is that the VNE of the
'high performance' aircraft you describe is specified
as IAS at cruising altitude - not at sea level. Therefore
your calculation of TAS being higher than VNE is flawed
because you have taken the wrong air density as your
datum.
So Vne of power planes is a figure which
describes Vne at the highest cruising altitude? So
this means that actual Vne at a lower altitude may
be faster? Hmmm...this seems to make sense for power
planes...
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