Journal ArticleDOI
Influence of Nose-Tip Bluntness on Conical Boundary-Layer Instabilities at Mach 10
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In this article, boundary-layer transition experiments are performed at the von Karman Institute for Fluid Dynamics in the lowenthalpy Longshot wind tunnel Freestream Mach numbers are within the rangeAbstract:
Hypersonic boundary-layer transition experiments are performed at the von Karman Institute for Fluid Dynamics in the low-enthalpy Longshot wind tunnel Freestream Mach numbers are within the range read more
Citations
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Journal ArticleDOI
Characterization of instability mechanisms on sharp and blunt slender cones at Mach 6
TL;DR: In this paper , the effect of nose tip bluntness on the instability mechanism leading to boundary-layer transition on a half-angle cone in a Mach-6 free stream was investigated using a combination of high-speed calibrated schlieren images and pressure measurements, and the data are compared with results computed using the parabolized stability equations.
Journal ArticleDOI
Experimental Measurements of Hypersonic Instabilities over Ogive-Cylinders at Mach 6
TL;DR: In this article , a curvature-based Reynolds number is proposed that successfully correlates the effects of multiple leading edge radii of curvature to dominant downstream boundary layer disturbances and transition onset locations.
Proceedings ArticleDOI
Implementation of Self-Aligned Focusing Schlieren for Hypersonic Boundary Layer Measurements
TL;DR: In this paper , a self-aligned focusing schlieren (SAFS) is implemented for the purpose of making near-planar density gradient measurements of hypersonic boundary layers.
Journal ArticleDOI
Cross-flow vortices and their secondary instabilities in hypersonic and high-enthalpy boundary layers
TL;DR: In this paper , the cross-flow primary and secondary instabilities in hypersonic and high-enthalpy boundary layers, considering thermochemical non-equilibrium (TCNE) effects, were investigated.
Proceedings ArticleDOI
Interaction of a Tunnel-like Acoustic Disturbance Field with a Blunt Cone Boundary Layer at Mach 8
TL;DR: In this article , the effects of freestream acoustic disturbances on transition reversal over a blunt body were investigated by both direct numerical simulations (DNS) and modal and nonmodal stability analysis, and the results showed that the broadband tunnel noise in the free stream of a convectional hypersonic wind tunnel (i.e., outside the nozzle-wall turbulent boundary layer) can be well represented by an acoustic model with an ansatz of slow plane acoustic waves.
References
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Journal ArticleDOI
Numerical methods for hypersonic boundary layer stability
TL;DR: In this article, the authors compared various numerical methods for the solution of linear stability equations for compressible boundary layers and discussed both the global and local eigenvalue methods for temporal stability analysis.
Journal ArticleDOI
Linear Stability Theory and the Problem of Supersonic Boundary- Layer Transition
TL;DR: In this paper, the amplitude ratio of constant-frequency disturbances as a function of Reynolds number for insulated and cooled-wall flat-plate boundary layers between Mach numbers 1.3 and 5.8 is calculated.
Journal ArticleDOI
Transition and Stability of High-Speed Boundary Layers
TL;DR: In this article, stability and laminar-turbulent transition in high-speed boundary-layer flows are discussed, emphasizing qualitative features of the disturbance spectrum leading to new mechanisms of receptivity and instability.
Journal ArticleDOI
Hypersonic laminar–turbulent transition on circular cones and scramjet forebodies
TL;DR: In this paper, the authors reviewed the literature for transition on circular cones and scramjet forebodies from an experimental point of view, focusing on the effect of laminar-turbulent transition in hypersonic boundary layers.