Quote:
Originally Posted by Kwiatek
Yea You right these charts are from NACA test. All these test have very low value of Cl max for all profiles so You should be right that test was made with small Reynolds Number.
These NACA data and test are very inaccurate for RL planes and airfoils.
I found some more reliable data for such airfoils:
Fokker DVII- 1.32 Clmax
RAF 15 ( SE5?) - 1.2 Clmax
Spad XIII - 1.05 Clmax
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Kwiatek,
can you please tell me the source (or web page) of that NACA test? Or the number and type of airfoil study (M.I.T., Eiffel, Gottinga ....).
I have about 1,000 airfoils charts from a 1925 italian official publication but many of them are identified only by number/study and not by aircraft.
Regards,
GATT