超临界自然层流机翼设计及基于TSP技术的边界层转捩风洞试验

To achieve the green aviation goal of energy conservation and emission reduction, laminar flow design technology has become the hot research area for aircraft designers. For transonic airliners, supercritical natural laminar flow wing design technology will significantly reduce the flight drag, improve aerodynamic performance, and decrease fuel consumption and pollutant emissions. Based on the high-precision boundary layer transition prediction technique, the airfoil optimization design system is applied to design the supercritical natural laminar flow airfoils. Then the airfoils are arranged rationally to form the supercritical natural laminar flow wing. Numerical simulations of the supercritical natural laminar flow wing show satisfactory laminar flow characteristics. Then, a model with ratio of 1:10.4 is used to test the boundary layer transition in high speed and low turbulence wind tunnel in Netherland. The Temperature Sensitive Paint (TSP) technique is used to photograph laminar-turbulent area distribution at different Mach numbers, Reynolds numbers and angels of attack. At last, the boundary layer transition characteristics of the supercritical natural laminar flow wing are discussed, and the key factors of the wing design are summarized. In addition, the model can also be used to verify the accuracy of the boundary layer transition prediction technique for supercritical and high Reynolds numbers condition.