Scale-effect tests in a turbulent tunnel of the NACA 653-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap
Publisher: Langley Memorial Aeronautical Laboratory
Published: 1944
Place of publication: Langley Field, VA
Language: eng
Number of pages: 32
Subjects: Reynolds number; Aerofoils; Aerodynamics--Research.
Description: <a href="http://uf.catalog.fcla.edu/uf.jsp?st=UF003613066&ix=nu&I=0&V=D&pm=1" rel="nofollow">http://uf.catalog.fcla.edu/uf.jsp?st=UF003613066&ix=nu&I=0&V=D&pm=1</a>