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Effects of Forward-Facing Step Shape on Stationary Crossflow Instability Growth and BreakdownThe effect of forward-facing step shape on stationary-crossflow growth was studied down-stream of a two-dimensional step in a swept-wing flow. The step height was set at 81% of the local unperturbed boundary layer thickness at the step location, and the shape was varied by placing two ramps of differing slopes upstream of the step: 30◦ and 45◦. The ramps were successful at delaying transition, with increasing success as the slope was decreased. The ramps significantly altered the mean flow, reducing or eliminating the separation region and crossflow-reversal region downstream of the step, which reduced the amplification of the stationary crossflow modes shortly downstream of the step. The mean flow modification induced by the step also had destabilizing effects that persisted farther downstream as the flow recovered from the near-step region. The downstream growth of the stationary crossflow instabilities was also mitigated by the introduction of the ramps upstream of the step. The presence of harmonics beginning near this region confirms previous findings that there are nonlinear interactions contributing to the growth of the instability.
Document ID
20200002613
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Jenna L Eppink ORCID
(Langley Research Center Hampton, United States)
Cody Casper
(University of Wisconsin–Milwaukee Milwaukee, United States)
Date Acquired
April 17, 2020
Publication Date
June 15, 2019
Publication Information
Publication: AIAA Aviation 2019 Forum
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Fluid Mechanics and Thermodynamics
Report/Patent Number
NF1676L-31492
AIAA-2019-3532
Meeting Information
Meeting: AIAA AVIATION Forum and Exposition
Location: Dallas, TX
Country: US
Start Date: June 17, 2019
End Date: June 21, 2019
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 109492.02.01.01.05
Distribution Limits
Public
Copyright
Use by or on behalf of the US Gov. Permitted.
Keywords
Laminar Separation Bubble
Swept Wing
Vortices
Separated Flows
Particle Image Velocimetry
Velocity Profiles
Adverse Pressure Gradient
Flight Testing
NASA Langley Research Center
Freestream Turbulence
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