Nonadiabatic Surface Effects on Transition Measurements Using Temperature-Sensitive Paints

Abstract

Tests were conducted at the Cryogenic Ludwieg-Tube Göttingen (DNW-KRG) to investigate the influence on onset of boundary layer transition of thermal gradients on the model surface, whereby the Temperature-Sensitive Paint technique has been used to detect transition. The laminar airfoil under investigation was tested at high Reynolds and at both low and high subsonic Mach numbers. The influence on boundary layer transition of the temperature difference between flow and model surface due to the temperature drop occurring during a run at DNW-KRG was examined. Various combinations of flow conditions and angles-of-attack were employed in order to investigate different stability situations. The unfavorable impact of surface temperatures larger than the adiabatic wall temperature was identified to be dependent on the considered boundary layer stability situation. For certain stability situations, it was shown that a non-adiabatic model surface can strongly influence the boundary layer transition location.