INVESTIGATION OF BOUNDARY-LAYER REYNOLDS NUMBER FOR TRANSITION ON AN NACA 65(215)-114 AIRFOIL IN THE LANGLEY TWO-DIMENSIONAL LOW-TURBULENCE PRESSURE TUNNEL

摘要

A low—turbulence wind—tunnel investigation was made of an aerodynamically smooth NACA 65（215）-114 airfoil having faired surfaces hack to 37 percent chord to determine the magnitude of the boundary—layer Reynolds number at various positions of transition from laminar to turbulent flow along both airfoil surfaces. In addition to boundary-layer measurements, values of the section drag coefficient were obtained by means of the wake—survey method.