Factors Influencing Pitot Probe Centerline Displacement in a Turbulent Supersonic Boundary Layer

摘要: When a total pressure probe is used for measuring flows with transverse gradients, displacement of the effective center observed (designated Delta). While this phenomenon well documented in incompressible flow and supersonic laminar flow, there insufficient information concerning turbulent flow. In study, three NASA Lewis Research Center Supersonic Wind Tunnels (SWT's) were to investigate pitot centerline boundary layers. The relationship between test conditions error was be determined. For investigation, ten circular probes diameter-to-boundary layer ratios (D/delta) ranging from 0.015 0.256 tested 10 ft x SWT, 15 cm 1 SWT. Reynolds numbers 4.27 10(exp 6)/m, 6.00 6)/in, 10.33 16.9 6)/m at nominal Mach 2.0 2.5. Boundary thicknesses tunnels approximately 200 mm, 13 30 respectively. Initial results indicate that thickness, delta, diameter, D/delta play minimal role offset error, Delta/D. It appears gradient, dM/dy, an important factor, though exact has not yet been More data needed fill map before conclusion can drawn any certainty. This research provides valuable supersonic, wind very different will prove stepping stone future into factors influencing error.