This paper presents the experimental investigations of NACA0012 airfoil aerodynamic characteristics improvement by airfoil tail tailoring ( 30% chord part ) in low speed wind tunnel. Experiment Renolds number range is 4.9 ×10 5 to 6.5 ×10 5 , and the angle-of-attack range is -12° to 12°. The comparisons of experimental results show that: tail tailoring can increase both airfoil lift and lift-to-drag ratio in the positive angle-of-attack range; it can decrease airfoil drag in the negative angle-of-attack range.

This paper presents the experimental investigations of high angle-of-attack flow control on NACA0012 airfoil using vortex-generating devices in low speed wind tunnel. The vortex-generating devices used are (i) top-surface triangular wing type vortex-generators, (ii) leading-edge vortex-generators, (iii) leading-edge slots. Experiment Renolds number range is 4.9×105 to 6.5×105 , the angle-of-attack range is-10° to 20°. The comparisons of experimental results show that the vortex-generating devices can dramatically improve airfoil aerodynamic characteristics at normal stall angle-of-attack by increasing both the lift and the lift-to-drag ratio.