Numerical Experiment of Flow Characteristics of Parallel Arrangement Two Symmetrical Airfoils

In this study, numerical experiment of flow around the close two airfoils which arranged in parallel with attack angle was performed. The aspect of flow and the instantaneous fluid force act on symmetrical airfoil (NACA0012) with attack angle were investigated using a vortex method at the Reynolds number Re=4.05×105, in ranges of the distance ratio L/c= 0.0, 0.25, 0.50 and 1.0 (here, L/c = 0.0 means single airfoil case) and the attack angle α = 0, 5, 10 and 15 degrees, (here, α =15 degree case is performed on single airfoil case only). As a result of calculations, in the case of two airfoils, the large lift was able to be obtained as compared with the single airfoil, but it was found in it that they are about 1.5 times in the case of single airfoil. And it was shown that the fluid force characteristic of each airfoil of two airfoils differs from the case of single airfoil.