Onset of vortex breakdown above a pitching delta wing. Visbal, M. R. AIAA Journal, 32(8):1568–1575, May, 2012. ![Onset of vortex breakdown above a pitching delta wing [link]](https://bibbase.org/img/filetypes/link.svg "link")
Paper doi abstract bibtex 7 downloads Computational results are presented for transient vortex breakdown above a delta wing subject to a pitch-andhold maneuver to high angle of attack. The flows are simulated by solving the full three-dimensional Navier- Stokes equations on a moving grid using the implicit Beam-Warming algorithm. An assessment of the effects of numerical resolution and favorable comparison with experimental data suggest the computational approach captures the basic dynamics of the onset and initial stages of transient breakdown. The pressure gradient along the vortex axis is found to play a dominant role in the initiation of breakdown. A description of the three-dimensional instantaneous structure of the flowfield is provided for the first time using critical-point theory. The reversed-flow region in the vortex core is associated with pairs of opposite spiral/saddle critical points. At its onset, the vortex breakdown is fairly axisymmetric; however, as it proceeds upstream and a stronger jump takes place along the axis, asymmetric effects become important and culminate in the formation of a bubble-type breakdown. This bubble structure is open and contains within itself a pair of stagnation points that are diametrically opposed and that rotate in the same sense as the upstream swirling flow. These critical points suggest the existence of azimuthal disturbances in the breakdown region. The bubble sectional topology is also found in agreement with recent experimental measurements. © 1994 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.
@article{visbal2012,
title = {Onset of vortex breakdown above a pitching delta wing},
volume = {32},
url = {https://arc.aiaa.org/doi/abs/10.2514/3.12145},
doi = {10.2514/3.12145},
abstract = {Computational results are presented for transient vortex breakdown above a delta wing subject to a pitch-andhold maneuver to high angle of attack. The flows are simulated by solving the full three-dimensional Navier- Stokes equations on a moving grid using the implicit Beam-Warming algorithm. An assessment of the effects of numerical resolution and favorable comparison with experimental data suggest the computational approach captures the basic dynamics of the onset and initial stages of transient breakdown. The pressure gradient along the vortex axis is found to play a dominant role in the initiation of breakdown. A description of the three-dimensional instantaneous structure of the flowfield is provided for the first time using critical-point theory. The reversed-flow region in the vortex core is associated with pairs of opposite spiral/saddle critical points. At its onset, the vortex breakdown is fairly axisymmetric; however, as it proceeds upstream and a stronger jump takes place along the axis, asymmetric effects become important and culminate in the formation of a bubble-type breakdown. This bubble structure is open and contains within itself a pair of stagnation points that are diametrically opposed and that rotate in the same sense as the upstream swirling flow. These critical points suggest the existence of azimuthal disturbances in the breakdown region. The bubble sectional topology is also found in agreement with recent experimental measurements. © 1994 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.},
number = {8},
journal = {AIAA Journal},
author = {Visbal, Miguel R.},
month = may,
year = {2012},
keywords = {Angle of Attack, Cambered Delta Wing, Flow Visualization Techniques, Freestream Mach Number, Navier Stokes Equations, Shear Layers, Streamlines Pattern, Taylor Vortex Flow, Velocity Profiles, Vortex Breakdown},
pages = {1568--1575},
}
Downloads: 7
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