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PRESSURE-SENSING PERFORMANCE OF UPRIGHT CYLINDERS IN A MACH 10 BOUNDARY-LAYER , Technical Memorandum Authors: Steven Johnson and Kelly Murphy Report Number: NASA-TM-4633 Performing Organization: NASA Dryden Flight Research Center, Edwards, CA Abstract: An experimental research program to provide basic knowledge of the pressure-sensing performance of upright, flush-ported cylinders in a hypersonic boundary layer is described. Three upright cylinders of 0.25-, 0.5-, and 1-in. diameters and a conventional rake were placed in the test section sidewall boundary layer of the 31 Inch Mach 10 Wind Tunnel at NASA Langley Research Center, Hampton, Virginia. Boundary-layer pressures from these cylinders were compared to those measured with a conventional rake. A boundary-layer thickness-to-cylinder-diameter ratio of 8 proved sufficient to accurately measure an overall pressure profile and ascertain the boundarylayer thickness. Effects of Reynolds number, flow angularity, and shock wave impingement on pressure measurement were also investigated. Although Reynolds number effects were negligible at the conditions studied, flow angularity above 10 deg significantly affects the measured pressures. Shock wave impingement was used to investigate orifice-to-orifice pressure crosstalk. No crosstalk was measured. The lower pressure measured above the oblique shock wave impingement showed no influence of the higher pressure generated at the lower port locations. Distribution/Availability: Unclassified - Unlimited Subject Category: 02 Availability:
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