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.