Effects of High-Speed Tunnel Noise on Laminar-Turbulent Transition

By S. Schneider. 2000

398 citations recorded by the source corpus.

Subfields: Aerospace Engineering, Computational Mechanics, Environmental Engineering

View Paper: https://www.semanticscholar.org/paper/c86ca9c520159064078d49f3a9361dd3dee24569

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Citations in the corpus

Breakdown mechanisms and heat transfer overshoot in hypersonic zero pressure gradient boundary layers (2013, background): “In addition, the fluctuations in noisy tunnels at lower frequencies typical of first mode instabilities have higher amplitudes than the frequencies typical of second mode instabilities (Schneider 2001).”
Fifty years of hypersonics: where we've been, where we're going (2003, background): “may invalidate most, if not all, hypersonic transition data that exists [24].”
Direct Numerical Simulation on the Receptivity, Instability, and Transition of Hypersonic Boundary Layers (2012, background): “…transition for circular cones, scramjet forebodies, and reentry capsules (Schneider 1999, 2004, 2006); the effects of high-speed tunnel noise on transition (Schneider 2001); and experimental and flight tests of the hypersonic boundary-layer transition with surface roughness (Schneider 2008a,b).”
Developing mechanism-based methods for estimating hypersonic boundary-layer transition in flight: The role of quiet tunnels (2013, background): “The bow shock that is present on realistic geometries converts freestream acoustic and vorticity perturbations into all other forms [32], so the low-speed information here must be adapted with care.”
Development of Hypersonic Quiet Tunnels (2008, background): “He reviews variousmeasurements that are discussed in [24] and leaves the question open, as it remains.”
Experiments on passive hypervelocity boundary-layer control using an ultrasonically absorptive surface (2002, background): “Schneider [105] reports that freestream turbulence levels measured in shock tunnels at lower frequencies (hundreds of kilohertz) are typically of the order of 1% to 3%.”
Effects of Roughness on Hypersonic Boundary-Layer Transition (2007, neutral): “5–1% of the mean, are an order of magnitude larger than those observed in flight [7,8].”
Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: fundamental breakdown (2015, background): “…in carrying out hypersonic boundary layer experiments (‘controlled’ experiments, in particular) and due to the existence of multiple instability modes, the role and importance of the various instability modes in a realistic transition process are not understood at all (see Schneider 2001, 2004).”