Boundary Layer Transition on Slender Cones in Conventional and Low Disturbance Mach 6 Wind Tunnels
By T. Horvath, S. Berry, B. Hollis, Chau-Lyan Chang, B. Singer. 2002
156 citations recorded by the source corpus.
Subfields: Aerospace Engineering, Computational Mechanics, Environmental Engineering
View Paper: https://www.semanticscholar.org/paper/7d06dd02096ab2229979d98f4d334fa3f12f5cb3
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In Aerospace Engineering
In Computational Mechanics
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Citations in the corpus
- Hypersonic laminar–turbulent transition on circular cones and scramjet forebodies (2004, background): “[52] for a case where the peak in heat transfer is only about 2/3 of the way to fully-developed turbulent heating.”
- Interactions between second mode and low-frequency waves in a hypersonic boundary layer (2017, methodology): “Experiments similar to the PKU experiments have been undertaken with various conditions (Lachwicz et al. 1996; Horvath et al. 2002; Berridge et al. 2010; Hofferth et al. 2013), and DNS/PSE simulations have been used to study the fundamental breakdown (Pruett & Chang 1998; Laible & Fasel 2011;…”
- Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: fundamental breakdown (2015, background): “The streamwise temperature distribution measured under noisy-flow conditions (see figure 11b in Berridge et al. 2010) was also different from the distribution measured under quiet-flow conditions: it increased gradually from the laminar value to the turbulent value (as in Horvath et al. 2002).”