Transition-related studies on two low-drag airfoils

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. Meas urements made included model pressure distributions and unsteady signals fr om surface mounted hot-films over an incidence range of 0-6 degrees. Chemic al 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.