Pedro Paredes
National Institute of Aerospace
111 Papers
211 Citations
Pedro Paredes is an academic researcher from National Institute of Aerospace. The author has contributed to research in topics: Boundary layer & Mach number. The author has an hindex of 16, co-authored 74 publications. Previous affiliations of Pedro Paredes include Technical University of Madrid & Langley Research Center.
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Papers
Laminar-turbulent transition induced by a discrete roughness element in a supersonic boundary layer
TL;DR: In this article, the linear instability and breakdown to turbulence induced by an isolated roughness element in a boundary layer at Mach 2:5, over an isothermal flat plate with laminar adiabatic wall temperature, have been analyzed by means of direct numerical simulations, aided by spatial BiGlobal and three-dimensional parabolized (PSE-3D) stability analyses.
Order 104 speedup in global linear instability analysis using matrix formation
TL;DR: In this paper, a unified solution framework is presented for one-, two-or three-dimensional complex non-symmetric eigenvalue problems, respectively governing linear modal instability of incompressible fluid flows in rectangular domains having two, one or no homogeneous spatial directions.
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Nose-Tip Bluntness Effects on Transition at Hypersonic Speeds
Pedro Paredes,Meelan M. Choudhari,Fei Li,Joseph S. Jewell,Roger L. Kimmel,Eric C. Marineau,Guillaume Grossir +6 more
TL;DR: The existing database of transition measurements in hypersonic ground facilities has established that as the nose-tip bluntness is increased the onset of boundary-layer transition over a circular c....
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Four Decades of Studying Global Linear Instability: Progress and Challenges
TL;DR: In this paper, a Jacobian-free Newton-Krylov time-stepping method was used to obtain global linear instability results in flows of industrial interest, and connections between established and more modern approaches for structure identification in flows, such as proper orthogonal decomposition and Koopman modes analysis (dynamic mode decomposition), were made.
Secondary instability analysis of crossflow on a hypersonic yawed straight circular cone
TL;DR: In this paper, the authors provide secondary instability analysis of stationary crossflow vortices on a hypersonic yawed straight circular cone with a half-angle at angle of attack, free-stream Mach number 6 and unit Reynolds number.
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