抄録
The pressure distribution on a NACA0012 airfoil was measured in order to clarify the flow field around the airfoil in the low-Reynolds-number region from 10,000 to 50,000. In the present study, a wind tunnel and a NACA0012 wing model with 70 static pressure ports were used for the measurements. The pressure on the airfoil surface was measured by a micro-pressure sensor. Based on the obtained pressure distributions, we confirmed in detail the behavior of the separation bubble and observed the change of a short bubble into a long bubble. As the angle of attack was increased, the non-linearity of the aerodynamic characteristics was affected by both changes in the separation point and the length of the separation bubble. We confirmed that the behavior of the separation bubble is affected by flow field phenomena that depend on the Reynolds number.
