Aerodynamic Characteristics at Reynolds Numbers of 3.0 x 10(6) and 6.0 x 10(6) of Three Airfoil Sections Formed by Cutting Off Various Amounts From the Rear Portion of the NACA 0012 Airfoil Section

摘要

An investigation has been made of the two-dimensional aerodynamic characteristics of three airfoil sections formed by removing l.5, 4.O, and l2.5 percent of the original chord from the trailing edge of the NACA 0012 airfoil section. The tests consisted of measurements of section lift, drag, and pitching-moment coefficients at Reynolds numbers of 3.0 x lO(6) and 6.O x 10(6) for the airfoil sections both in the smooth condition and with roughened leading edges. The characteristics of the airfoil section obtained by cutting off l.5 percent chord were also determined with a spanwise row of rivet heads on each surface near the trailing edge.