要約

The problem of the creation of high-speed supercritical airfoils with reduced level of drag at high subsonic speeds is considered. The conception proposed consists of a tangential blowing of a high-pressure, low-intensity jet for elimination of wave separation. This wave separation is due to the shockwave which closes the local supersonic area on an airfoil. Computational evaluations of the possibility of drag reduction for supercritical second-generation airfoils with the low level of wave drag under turbulent flow conditions by means of tangential jet blowing on the upper and lower surfaces at c_y = 0.55 and Re = 40 × 10⁶ within the Mach number range M = 0.7 ÷ 0.88 are fulfilled.