抄録
Boundary-layer transition measurements on an unswept wing of the Beechcraft Model 65 airplane in flight test were done prior to the launch of the NAL SST Non-Powered Experimental Airplane (NEXST). The main objectives of this experiment are to establish both measurement and diagnosis techniques for detecting the transition location by means of hot-film sensors, which are the similar type of sensors installed on the main wing of NEXST. A series of hot-film measurements showed a transition process, which is commonly seen in low-turbulence wind-tunnel tests. That is, although the output level of a hot-film at the beginning of transition was quite low, further downstream sensors detected unstable Tollmien-Schlichting waves, which finally led to turbulence. It was also observed that the center frequency of this instability wave is predictable.
