A description is given of test capabilities which have been developed for efficient flow fluctuation measurements using hot-wire anemometry techniques AEDC-VKF supersonic and hypersonic wind tunnels. Data acquistion is facilitated by push button switching among preset wire heating currents and magnetic tape recording of the sensor response signal. Real-time analysis of the signal is available for monitoring during measurements, and subsequent detailed analysis is performed using the tape record. Auxiliary systems have been fabricated which permit model boundary-layer surveys to be made in steps as small as 0.001 in. Optical techniques have been developed that make it possible to monitor and measure probe position relative to the model surface in 0.001-in. increments. Representative results obtained in two series of boundary-layer studies using these capabilities at free-stream Mach numbers of 6 and 8 are shown.
