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The Effect of Backward-Facing Step Height on Instability Growth and Breakdown in Swept Wing Boundary-Layer TransitionA low-speed experiment was performed on a swept at plate model with an imposed pressure gradient to determine the effect of a backward-facing step on transition in a stationary-cross flow dominated flow. Detailed hot-wire boundary-layer measurements were performed for three backward-facing step heights of approximately 36, 45, and 49% of the boundary-layer thickness at the step. These step heights correspond to a subcritical, nearly-critical, and critical case. Three leading-edge roughness configurations were tested to determine the effect of stationary-cross flow amplitude on transition. The step caused a local increase in amplitude of the stationary cross flow for the two larger step height cases, but farther downstream the amplitude decreased and remained below the baseline amplitude. The smallest step caused a slight local decrease in amplitude of the primary stationary cross flow mode, but the amplitude collapsed back to the baseline case far downstream of the step. The effect of the step on the amplitude of the primary cross flow mode increased with step height, however, the stationary cross flow amplitudes remained low and thus, stationary cross flow was not solely responsible for transition. Unsteady disturbances were present downstream of the step for all three step heights, and the amplitudes increased with increasing step height. The only exception is that the lower frequency (traveling crossflow-like) disturbance was not present in the lowest step height case. Positive and negative spikes in instantaneous velocity began to occur for the two larger step height cases and then grew in number and amplitude downstream of reattachment, eventually leading to transition. The number and amplitude of spikes varied depending on the step height and cross flow amplitude. Despite the low amplitude of the disturbances in the intermediate step height case, breakdown began to occur intermittently and the flow underwent a long transition region.
Document ID
20160005988
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Jenna L Eppink ORCID
(Langley Research Center Hampton, United States)
Richard W Wlezien
(Iowa State University Ames, United States)
Rudolph A King ORCID
(Langley Research Center Hampton, United States)
Meelan Choudhari ORCID
(Langley Research Center Hampton, United States)
Date Acquired
May 10, 2016
Publication Date
June 18, 2015
Publication Information
Publication: 45th AIAA Fluid Dynamics Conference
Publisher: American Institute of Aeronautics and Astronautics
Subject Category
Fluid Mechanics and Thermodynamics
Report/Patent Number
NF1676L-20019
AIAA-2015-2776
Meeting Information
Meeting: AIAA AVIATION Forum and Exposition
Location: Dallas, TX
Country: US
Start Date: June 22, 2015
End Date: June 26, 2015
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 794072.02.07.02.02
Distribution Limits
Public
Copyright
Use by or on behalf of the US Gov. Permitted.
Keywords
Angle of Attack
Freestream Velocity
Freestream Turbulence
Parabolized Stability Equations
Wind Tunnel Models
Vortices
Turbulent Flow
Pressure Coefficient
Aircraft Wings
Boundary Layer Transition
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