Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap Page: 19 of 22
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
NACA ACR No. L4122
Fig. 4a, b
-/ .-. .3 , .j . ./.0 7/.
Peyna/ds n ze4 R
/Faure 4 - Sc/ effect on /f/-curve slope of
fte VACA 653-4/8 a/rfo/ second.
COMMITTEE FOR AERONAUTICS.
A _A'de ,
... . ... . 6
.2 .3 .4 .5 .6 .7.6.qa 0
/Pey o/s nVm er,
() A/ap effecte. oCa O&.
F/ure 4. - Co c/uaed
2.0 30 40/Ox
/ A 3 " r f- 4l 0A " JAA A
II Ill II I I II I II I i i , li, , , , .. ... .
Here’s what’s next.
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Tucker, Warren A. & Wallace, Arthur R. Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap, report, September 1944; (digital.library.unt.edu/ark:/67531/metadc61404/m1/19/: accessed December 16, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.