It has been indicated that the aerodynamic drag decreased and the lift increased at stall and post-stall angles of attack when the HF dielectric barrier discharge was turned on. The power delivered to discharge was modulated with a frequency of 3 × 102–2 × 104 Hz, which corresponds to a Strouhal number of St = 1.2–80, and the average electric power (WĪv) was 50–400 W. 1(b), to simulate the jet flow, a duct was used and inclined with respect to xy reference jet equal to 13.6 that corresponds to a jet angle jet equal to 30.2 between the exit jet and the airfoil surface. The effect of the surface capacity HF discharge on airfoil flow-around has been studied in the situation when the oncoming flow velocity is 20 m/s and the Reynolds numbers are Re = 105. The stalling characteristics of the two roughness and one streamwise ice simulation maintained the abrupt leading-edge stall type of the clean NACA 23012 airfoil, despite the significant decrease in maximum lift. The power delivered to discharge was modulated with a frequency of 3 × 1022 × 104 Hz, which corresponds to a Strouhal number of St 1.280, and the average electric power (W av) was 50400 W. lift values in the range of 1.09 to 1.28, which was a relatively small variation compared to the differences in the ice geometry.
10 shows that the values for drag coefficient are lower at higher Reynolds numbers for the range. Aerodynamic quality management for the NACA 23012 airfoil model using the surface high-frequency discharge Aerodynamic quality management for the NACA 23012 airfoil model using the surface high-frequency.īityurin, V. The effect of the surface capacity HF discharge on airfoil flow-around has been studied in the situation when the oncoming flow velocity is 20 m/s and the Reynolds numbers are Re 105. The stalling angle is constant at 14, for all the Reynolds number ranges.