Experimental results of boundary layer transition locations on two low-drag airfoils tested in the NAL 1.5 m low speed wind tunnel are presented. Measurements made included model pressure distributions and unsteady signals from surface mounted hot-films over an incidence range of 0-6 degrees. Chemical sublimation technique was also utilized to infer location of transition in one of the studies. The experimental results on transition location are discussed and compared with earlier data available in the literature. [References: 6]
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