DESIGN OF MEASUREMENT SETUP FOR HIGH-ALTITUDE IN-FLIGHT EXPERIMENTS ON DU89-134/14 AIRFOIL AT LOW REYNOLDS NUMBER

Two measurement setup configurations for high-altitude in-flight experiments are evaluated, with the configuration where the test airfoil is mounted vertically under the test aircraft wing showing clear advantages. The test airfoil design as well as the design of systems architecture based on the aforementioned configuration is presented. The steady 3D RANS numerical simulations with the transitional (γ −Reθ ) SST turbulence model have been used to examine the effects of the test aircraft on the flow field around the test airfoil. Based on the analysis of the pressure and skin friction coefficient distributions it can be concluded that the flow field around the test airfoil is uniform between between s/c = 0.29 to s/c = 0.71.