The test with a roughness application on the laminar aerofoil has been conducted in the N-3 trisonic wind tunnel
of the Institute of Aviation in Warsaw. The main goal of tests was to investigate the influence of the boundary layer
transition triggers on a laminar profile aerodynamic characteristic. For baseline configuration, the natural transition
was applied. As a local roughness on the upper model surface, the carborundum strips with different heights were
applied. These were positioned on the upper model surface in the front of the shock position occurrence. The Mach
number during test was equal Ma = 0.7 and Reynolds number was about 2.85·106
. Tests have been conducted for
different model incidence in range 0º-7º. Current article refers partially to the previous study, where aerofoil model
with lower quality of surface had been tested. Investigation results from previous work indicated that some of
transition positions improved an aerodynamic characteristic by reducing the drag coefficient value and decreasing
shock wave unsteadiness in the transonic regime. However, current article indicates that beneficial effects in respect
to the baseline configuration are also strictly dependent on the model quality and turbulent triggers size. Improved
surface quality of the laminar aerofoil model affected on aerodynamic characteristics with and without turbulent
triggers. Resultant aerodynamic coefficients of all tested cases i.e. drag, lift and lift to drag ratio were compared.
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