![]() Flow was nominally maintained at Mach 10 and a stagnation temperature of 1250 K (2250°R). The skin friction sensor was integrated into a steel 155.6-cm-long (61.27 in.-long), 7 deg half-angle cone model. The main investigations were conducted in Arnold Engineering Development Complex Tunnel 9. Validation testing was conducted in a supersonic tunnel at Mach 4.0. The calibration process characterized static, thermal, pressure, and dynamic responses. The sensors underwent National Institute of Standards and Technology traceable calibrations with well-documented uncertainties. A multistep approach tested the sensors through bench-test and wind-tunnel facilities. This investigation concerns the design, build, and testing of direct-measuring skin friction sensors capable of performing in sustained hypersonic flow and detecting transition.
0 Comments
Leave a Reply. |
Details
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |