I just noticed that there might be/is a typo in the ch53e-yasim.xml file.
change:
ground-effect-constatnt=1.25
to:
ground-effect-constant=1.25
Greetings,
Wim
On 1/3/07, wim van hoydonck [EMAIL PROTECTED] wrote:
Hi there,
I just checked Janes' All the world aircraft (versions 1979-1880 and
Hi Wim,
wim van hoydonck schrieb am 19.12.2006 23:44:
The minimum pitch angle at the blade root (or pitch bearing) for most
helicopters is somewhere around 0 degrees, sometimes a bit more,
sometimes a bit less. This is probably dictated by airworthiness
requirements related to autorotational
If I got you correctly, the tip of the rotor for most helicopters has
negative pitch at minimum collective (equal to the twist, e.g. -8.5° for
the bo, -9 ... -12° for the ch47).
Indeed.
On ground most helicopters are parked
with collective full down. Therefore it should be possible, to find
Hi,
wim van hoydonck schrieb am 20.12.2006 21:48:
If I got you correctly, the tip of the rotor for most helicopters has
negative pitch at minimum collective (equal to the twist, e.g. -8.5° for
the bo, -9 ... -12° for the ch47).
Indeed.
On ground most helicopters are parked
with
Hi Maik,
yes, but it is still the double value than the bo. But the incidence
data I have for the bo is measured at 0.7r and therefore much smaller.
[...]
I am not sure if that matches the data. With 8° twist and -1.4° pitch at
minimum you will get -9.4° at the tip and something about -7°
Hi Joacim,
Joacim Persson schrieb am 19.12.2006 02:39:
On Tue, 19 Dec 2006, Maik Justus wrote:
One important point for the simulation: most rotors have a delta3 effect
(this means: reducing the pitch with increased flapping angle). Do you
know this parameter for the ch53e (or for other
Hi Wim,
wim van hoydonck schrieb am 19.12.2006 11:31:
Hi Maik,
yes, but it is still the double value than the bo. But the incidence
data I have for the bo is measured at 0.7r and therefore much smaller.
[...]
I am not sure if that matches the data. With 8° twist and -1.4° pitch
On Tue, 19 Dec 2006, Maik Justus wrote:
Important info for the ch47d flight model. I had expected a large delta3
effect. Can you point me to the point in the report, where you found
this info?
From the British ministry of defence:
Hi there,
Some data for the CH53e yasim model, taken from Prouty [1], p. 699.
Looking at the data in cvs, rotor diameters and chords should/could be
changed, just like control input ranges for the main and tail rotor.
Weights (lb):
- Empty:33009
- MTOW
Hi Wim,
very interesting data. I have googled to find out, which values are
correct, at least for the rotor diameter there is many data on the net.
It seems, that in the version in cvs some data are from the ch53d (or
are there different ch53e variants?). Very surprising for me are the
Hi Maik,
Once our library opens again next year (they are moving to a new
building), I'll cross check that data with Janes (I work at the
faculty of aerospace engineering in Delft).
Very surprising for me are the
cyclic/ collective data with approx 20+18=38 degree maximum incidence of
the
Hi Wim
wim van hoydonck schrieb am 18.12.2006 23:23:
Hi Maik,
Once our library opens again next year (they are moving to a new
building), I'll cross check that data with Janes (I work at the
faculty of aerospace engineering in Delft).
very good, thank you!
Very surprising for me are
On Tue, 19 Dec 2006, Maik Justus wrote:
One important point for the simulation: most rotors have a delta3 effect
(this means: reducing the pitch with increased flapping angle). Do you
know this parameter for the ch53e (or for other helicopter?)
I can only add that the CH-47D has no delta3
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