Ta 152H speed discrepancy

[moot]

SD67 has all the foil data you should need.. He just needs to find the root and tip chord data.  Says he can work out as many drag polars as you might want.   

[Stoney]

We don't need the drag polars for the airfoil--I can do that myself.  Where did he get his information on the Ta-152H airfoil?  Originally we were looking for the zero-lift drag coefficient for the Ta-152H when we started looking at this.  I was merely making an observation--it won't really bear on anything going forward other than simple trivia...

[33Vortex]

The Ta152H airfoil if you need to do in-depth analysis.


152 airfoil

[Stoney]

Not to be obtuse, but you're sure this is for the H and not a C?

[moot]

I don't have complete blueprints yet, so I can't tell myself.

[Stoney]

I suppose ultimately, we'd need a dimensioned drawing of the Ta-152H wing root.  The one in the .tif file Vortex sent is a NACA 23000 profile--I can tell without a translation--its a very distinctive shape.

[33Vortex]

I'm pretty sure, though not 100%, that it is a H airfoil but can verify with Hermann if you want to be absolutely sure.

Here is some more data. Ta152 airfoil

[33Vortex]

Is this the wingroot info you are looking for?

I'll remove these links so... wingroot

[gripen]

The FW drag data gives the polar as function of the flat plate area and Cl. As example in the case of the Ta 152H at high speed, the flat plate area is given as 0,502m2 and value of the K as 0,95. These can be converted to dimensionless form by dividing with wing area 14,44m2, thus Cd0=0,021545 and K=0,040773 (=> e=0,87).