Title: Scale-effect tests in a turbulent tunnel of the NACA 653-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap
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>
Subjects: Reynolds number, Aerofoils, Aerodynamics--Research.