Staudruck

Hello,

I need some data for the Franz-Xaver Worthmann profile FX 63-137. I don't mean the coordinates but aerodynamic data. I could find a lot of information on lift and drag for different Reynolds numbers but nothing on the moments cM. Does someone have this information. I need it for the layout of the horizontal stabilizer.

Thank's

HighPlains

My Feedback: (1)

You must be designing for Reynolds numbers in the 250,000 to 750,000 range.

My book shows that it has a pitching moment of -0.185 at a design lift coefficient or 0.6

Just have that single point of data, no graphs

EagleOne

What's the model you will be using this airfoil into?? Depending on the model size and application, it's not worth the hassle....

Staudruck

We are planning to build an UAV aircraft with relatively high wing loading and low approach speed, that means high c_Lmax. That's the reason why we think about the FX63-137. Minimal Reynolds number is about 200.000.
As far as I know the airfoil was developed for low Re-numbers, is that right?

I have data for lift and drag for different Re-numbers but no information on moment coeficient (must be quite high). Would be nice to have Cm0 and Cmalpha (moment gradient) to estimate the stability of the wing/tailplane configuration and to calculate the right c.g. location.

My idea was to use XFOIL to determine the moment coeficients for diferent angles of attack, but I have only very few experience on XFOIL. Perhaps there is someone out there, that could help?

Thank you very much.

EagleOne

XFOIL is a great program really. Although a little diffcult to use... And very accurate too, just keep the Re number above 120 000 and it's pretty reliable. If you want, I can give you a detailed explanation on how to analyse the airfoil with it. It's simple once you know the basics.

NFOOTE

If you need the data, you can download it from UIAC site. Has the Drag bucket diagrams also

Brian

Staudruck

Hello Brian: do you mean UIUC? Tried to find the data there, but couldn't find them. Only links to buy the books (perhaps no bad idea). Do you have the data (remember I need the moments)?

Rodrigo: I would be happy if you could teach me some more XFOIL. I tried to simulate a NACA0009 airfoil at Re 200.000 but failed to obtain the right cL values. So I am distrusting a bit my capabilities. The only manual I have, is the manual you find on Drela's Homepage. Is there any book that describes the program more in detail? Do you have something more detailed? I would be happy to know more about how the program works.

Thanks

Frank

BFoote

lets see, the book costs all of what $20? Last I checked you pay people for the work that they do. Yes, I have the data. I have it in both book, and digitial form and no, I will not give it to you. If its a school project, which it probably, is buy the book. Your schooling costs you how much a year and you are quibbling about $20 that will teach you more than you will ever learn in the classroom. If I am wrong and you are a UAV company, buy the book, besides there are quite a few airfoils better than the FX 63-137 for L/D at those RE#

Brian

davidfee

Frank,
Here you go. These were calculated with XFoil, using Profili as the interface.


Brian,
What are you trying to do? Make friends or something? Sheesh!


-David

nIgHthAwK17

Sounds like an airfoil for the SAE heavy-lift competition to me...

Hey Brian, don't know if you're an Aero major or not, but if you were, you'd know for every airfoil there is a purpose, and their purpose might be best fulfilled with what they have picked. As for the coefficient of moment number, it IS really important that they have it for what they're designing..

Hey Frank, if it is for SAE, what school are you competing for? I'm from Mississippi State and we'll be competing for the first time this year. Oh, and as for the XFOIL data - don't take it for absolute - we've got the Selig books with that data in it, and they say that XFOIL overshoots some of CL values at such a low Re. Something to keep in mind.

--CG

destructiveTester

from

http://www.nasg.com/afdb/plshow.phtml?n=6&file1=fx63137b-100800-uiuc.dat&comm1=FX63137(Re=100800,UIUC)&file2=fx63137b-155600-uiuc.dat&comm2=FX63137(Re=155600,B,UIUC)&file3=fx63137a-200100-uiuc.dat&comm3=FX63137(Re=200100,UIUC)&file4=fx63137b-200700-uiuc.dat&comm4=FX63137(Re=200700,B,UIUC)&file5=fx63137a-299500-uiuc.dat&comm5=FX63137(Re=299500,UIUC)&file6=fx63137b-308600-uiuc.dat&comm6=FX63137(Re=308600,B,UIUC)


and as far as I know, Dr Selig and co's data is freely available - you can get it all in pdf format online.

NASG have bothered to put the data online, which is very useful for people like me who just design RC aircraft (non-commercially).

tkekesi

Hi!

I am trying to run simulations in Edge on this profile for my master thesis, but realized on the way there that the coordinates available on the web give a 'wavy' geometry. Do you maybe know if there are different set of data available for the same profile, or how to get the function itself?

Thanks
Timi

UStik

Just try this, it's called "FX 63-137 13,7% smoothed" but I have no idea if it's really smooth. Rename .txt to .dat, it's the common dat format.

Addendum: Maybe it only looks wavy because there is no antialiasing in the programs you use to display the outline. The pixel steps might fool us. Here's how it looks converted to DXF and displayed with the SolidWorks viewer. And here's the coordinate table and pencil drawing from the wind tunnel department of Stuttgart University where FX Wortmann worked.

tkekesi

Thanks! I think this one is better than the one that's easy to find onthe web. We actually run a simulation on that one already, and youcould see the wavyness on the pressure. Hope this one will work though!

Timi