Skin-Friction Measurements at Subsonic and Transonic Mach Numbers with Embedded-Wire Gages
Final rept. Oct 1978-Mar 1980
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Embedded-wire skin-friction gages were tested in the Acoustic Research Tunnel ART and on a model in Tunnel 16T at AEDC. The range of Mach numbers and Reynolds numbers considered was typical of the conditions encountered in transonic wind tunnel testing. Data obtained by the embedded-wire technique agreed well with data from conventional methods of measuring skin friction when the gages were calibrated in situ. When the gages were calibrated and reinstalled at a later data, the calibration coefficients could not be corrected by simple techniques.
- Test Facilities, Equipment and Methods