stall speed is too high for the ta152

[niklas]

i tested the stall speed of the 190D and Ta152 (max. fuel load)
TA152: 107mph
190D: 110mph

the corresponding lift factors are:
Cl (152) : 1,56
Cl (190D) : 1,52

The problem is that the Ta152 had a modified airfoil compared to the 190A and D series. I put together the most important factors:
 

You can see in the last line Clmax (= Camax) which is higher for the Ta152 (1,7). The reason is that the point of the maximum thickness for the airfoil is moved forward (ta/tw =0,35 compared to 0,545 of the dora) which allowed obviously higher Cl-max factors.

And this is maybe, together with the larger wingarea, the reason why the 152 is not so fast. It was the opposite way compared to a laminar wing, where the point of maximum thickness was moved back.
Well, the drag is modelled, so what about the lift?

niklas

[Naudet]

hi Niklas, can u sent me the data sheet .jpg u used for this post via email.

Cause i am collecting .jpgs of original FW documents.

If yes, sent em to LNhome@gmx.net.

Ty

[SageFIN]

 

Originally posted by niklas:

Well, the drag is modelled, so what about the lift?

Well what do you think the stall speed should be then? I at least feel that the Ta-152 turns way better than any of the 190 series and it doesn't even have any power advantage versus the 190D9.

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SageFIN

"I think IŽll believe in Gosh instead of God.  If you donŽt
 believe in Gosh too, youŽll be darned to heck."
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[wells]

I think you misinterpreting that data Niklas?

All of them use the NACA 230xx series airfoil where the thickest part of the wing is 30% chord.  The ta/tw is the taper ratio (tip chord/root chord).  Given the cl values, only the thickness was different, probably 15% average for the Ta-152 and 12% average for the 190s.

Stall speed would be 46 m/s (103 mph) for the 152 and 49 m/s (109 mph) for the 190D-9.