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The Effect of Forward-Facing Steps on Stationary Crossflow Instability Growth and BreakdownThe effect of a forward-facing step on stationary crossflow transition was studied using standard stereo particle image velocimetry (PIV) and time-resolved PIV. Step heights ranging from 53 to 71% of the boundary-layer thickness were studied in detail. The steps above a critical step height of approximately 60% of the boundary-layer thickness had a significant impact on the stationary crossflow growth downstream of the step. For the critical cases, the stationary crossflow amplitude grew suddenly downstream of the step, decayed for a short region, then grew again. The adverse pressure gradient upstream of the step resulted in a region of crossflow reversal. A secondary set of vortices, rotating in the opposite direction to the primary vortices, developed underneath the uplifted primary vortices. The wall-normal velocity disturbance (V' ) created by these secondary vortices impacted the step, and is believed to feed into the strong vortex that developed downstream of the step. A large but very short negative crossflow region formed for a short region downstream of the step due to a sharp inboard curvature of the streamlines near the wall. For the larger step height cases, a crossflow-reversal region formed just downstream of the strong negative crossflow region. This crossflow reversal region is believed to play an important role in the growth of the stationary crossflow vortices downstream of the step, and may be a good indication of the critical forward-facing step height.
Document ID
20180002093
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Jenna L Eppink ORCID
(Langley Research Center Hampton, United States)
Date Acquired
March 23, 2018
Publication Date
January 8, 2018
Publication Information
Publication: 2018 AIAA Aerospace Sciences Meeting
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Fluid Mechanics and Thermodynamics
Report/Patent Number
NF1676L-28876
AIAA-2018-0817
Meeting Information
Meeting: AIAA SciTech Forum
Location: Kissimmee, FL
Country: US
Start Date: January 8, 2018
End Date: January 12, 2018
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 109492.02.07.01.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
NASA Langley Research Center
Nacelles
Band Pass Filter
Transport Aircraft
Adverse Pressure Gradient
Boundary Layer Thickness
Natural Laminar Flow
Swept Wing
Particle Image Velocimetry
Vortex Strength
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