Hypersonic Tripped Boundary Layer Measurements using FLEET Velocimetry

Pehrson, John C.; Leonov, Boris S.; Miles, Richard B.; Limbach, Christopher; Lakebrink, Matthew T.

doi:10.2514/6.2022-3477

Cited by 3 publications

(3 citation statements)

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“…A second theory considered, but ultimately dismissed, was that a counterrotating vortex pair maintained coherence to the measurement location 137.5 mm behind the tripping array where it was captured in mean velocity profile. Later measurement performed on flat plate models in the ACE tunnel using wallnormal FLEET showed no evidence of a counter-rotating vortex pair at similar downstream locations from the same tripping array [23,24].…”

Section: Wall-normal Fleet Velocimetrymentioning

confidence: 95%

“…This simulation serves to provide a fully-developed turbulent boundary layer with which to compare the FLEET measurements of the actual flow field. The generation of the model and the reasoning behind these assumptions are detailed by Pehrson et al [23].…”

Section: Wall-normal Fleet Velocimetrymentioning

confidence: 99%

“…The primary objective of this paper is the characterization of boundary layer transition to turbulence due to discrete roughness elements as a precursor to future studies [23,24] of shock-boundary layer interactions in the Actively Controlled Expansion (ACE) hypersonic wind tunnel at Texas A&M University. For this purpose, the authors have applied the FLEET MTV technique to measure velocity profiles behind the tripping array over 21 wind tunnel entries.…”

Section: Introductionmentioning

confidence: 99%

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Hypersonic FLEET velocimetry and uncertainty characterization in a tripped boundary layer

Pehrson,

Leonov,

Melone

et al. 2023

Meas. Sci. Technol.

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Femtosecond laser electronic excitation tagging (FLEET) velocimetry is applied in a hypersonic boundary layer behind an array of turbulence-inducing trips. One-dimensional mean velocity and root-mean-square (RMS) of velocity fluctuation profiles are extracted from FLEET emissions oriented across a test article and through a boundary layer in two test campaigns spanning 21 tunnel runs. The Texas A&M University Actively Controlled Expansion tunnel in which FLEET was performed operates near Mach 6.0 with Reynolds number near 6 ×106 m-1 and a working fluid of air at a density near 2.5 × 10-2 kg/m3. Calibration curves are generated using synthetic images to estimate the error in the mean velocity due to emission decay and the error in the RMS velocity fluctuation due to imprecision. The boundary layer behind an array of turbulence-inducing trips is documented to show the breakdown of coherent structures. FLEET velocimetry is compared to the tunnel data acquisition system, Vibrationally Excited Nitric Oxide Monitoring (VENOM) results, and Reynolds-Averaged Navier-Stokes Computational Fluid Dynamics to verify results.

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Section: Wall-normal Fleet Velocimetrymentioning

confidence: 95%

Section: Wall-normal Fleet Velocimetrymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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