Question for Yo-Yo about Fw 190 Clmax and cAoA? - Page 3 - ED Forums
 


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Old 10-06-2016, 05:37 AM   #21
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Keep in mind that the same influences will occur with the P-51 which smooth/polished model recorded a Clmax of 1.39 at NACA, whiilst the F6F recorded one of 1.60.

Just for reference.

FW AG's figures are probably for a smooth & polished airframe also, which was std. procedure anyway AFAIK.
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Old 04-18-2017, 05:07 PM   #22
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Quote:
Originally Posted by Pilum View Post

“Conclusions

In the large Chalais-Meudon wind tunnel, a full sized Fw 190 was tested.

Without split flap deflection the Camax turned out to be 1.3 and with 58 degrees split flap deflection Camax=1.55. These values are 0.3 to 0.4 lower than those of smooth/polished models. The deviation is due to the influence of fuselage, supports, and deviations in the wing profile shape.”

So at the Chalais Meudon wind tunnel Re of 4.6M the Clmax is 1.3 which given that an IRL stall speed Re is around 6.4M makes a Clmax at that Re in the order of 1.35-1.4 quite plausible.

So, it looks like this report backs up Yo-Yo’s choise of a Clmax in the range of 1.35 to 1.38 quite nicely!
The FW-190 simply cannot fly at that velocity so how can anyone conclude that is the CLmax??

Quote:
These values are 0.3 to 0.4 lower than those of smooth/polished models. The deviation is due to the influence of fuselage, supports, and deviations in the wing profile shape.”
This is not a retraction of earlier data but a statement that all the data agrees!!

1.3 + .3 or .4 = 1.6 to 1.7

In other words, the 1.58 for the clean configuration FW-190 CLmax is correct. That is why Focke Wulf used it. This is part of the parametric studies the wing design article refers too, btw.

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Old 04-19-2017, 08:22 AM   #23
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What Clmax is actually being used in the DCS Dora ?

It affects the stall characteristics of the aircraft, and overall situations where maximum lift generation is required.

It's very important for us glider pilots, on pair with the Reynolds number.
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Old 04-19-2017, 02:36 PM   #24
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Haven't we been down this road before?
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Old 04-19-2017, 02:42 PM   #25
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Groundhog Day...

https://www.youtube.com/watch?v=gtXULK1I9tk
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Ніщо так сильно не ранить мозок, як уламки скла від розбитих рожевих окулярів
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Ничто так сильно не ранит мозг, как осколки стекла от разбитых розовых очков (С) Me
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Old 04-19-2017, 09:02 PM   #26
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Mercury is in Retrograde.
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Old 05-03-2017, 12:01 AM   #27
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Velocity = (4900000*.000156927ft^2/sec )/5.95ft = 129.23 Ft/sec

129.23 Ft/sec = 87 mph...

Is the stall speed of an FW-190A only 87 mph?




Quote:
Mercury is in Retrograde.
Could be.....
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Old 05-03-2017, 12:07 AM   #28
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Quote:
Originally Posted by SkateZilla View Post
Mercury is in Retrograde.
Btw...

There are so many ways one could go with this.

Mercury could so easily be substituted with:

Credibility

Science

Engineering

Flight Mechanics

Anyway, it probably better if you stuck to an informed discussion using facts and not bait.

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Old 05-03-2017, 12:11 AM   #29
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Quote:
Originally Posted by Crumpp View Post
Velocity = (4900000*.000156927ft^2/sec )/5.95ft = 129.23 Ft/sec

129.23 Ft/sec = 87 mph...

Is the stall speed of an FW-190A only 87 mph?






Could be.....
Did we get a 190A in the sim and I missed it? Cool...
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Old 05-03-2017, 02:35 PM   #30
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Quote:
Originally Posted by SiThSpAwN View Post
Did we get a 190A in the sim and I missed it? Cool...


Yeah you missed the fact it is the same airfoil selection and wing design

Engineering wise, they will have the same CLmax and lift distribution.

An anton does not stall at 87 mph and neither does a Dora.




If you know the basic relationship of Reynolds Number to CLmax....

It is a simple fact the higher Reynolds that the FW-190 series stalls at requires a higher CLmax.
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