Design and Implementation of the Boundary Layer Transition Flight Experiment on Space Shuttle Discovery

Spanos, Theodoros A.; Micklos, Ann M.

doi:10.2514/6.2010-242

Cited by 4 publications

(1 citation statement)

References 3 publications

(8 reference statements)

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“…A recent paper describes the BLT Flight Experiment in much greater detail.' 5 Futhermore, the Hypersonic Thermodynamic Infrared Measurements (HYTHIRM) flight experiment obtained infrared images of the Orbiter windward side during three re-entries (missions STS-119, -125 and -128). These images have been converted to quantitative surface temperatures, and represent another important dataset for code assessment.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic Navier Stokes Comparisons to Orbiter Flight Data

Candler¹,

Campbell

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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During the STS-119 flight of Space Shuttle Discovery, two sets of surface temperature measurements were made. Under the HYTHIRM program 3 quantitative thermal images of the windward side of the Orbiter with a were taken. In addition, the Boundary Layer Transition Flight Experiment 4 made thermocouple measurements at discrete locations on the Orbiter wind side. Most of these measurements were made downstream of a surface protuberance designed to trip the boundary layer to turbulent flow. In this paper, we use the US3D computational fluid dynamics code to simulate the Orbiter flow field at conditions corresponding to the STS-119 re-entry. We employ a standard two-temperature, five-species finite-rate model for high-temperature air, and the surface catalysis model of Stewart. 1 This work is similar to the analysis of Wood et al .2 except that we use a different approach for modeling turbulent flow. We use the one-equation Spalart-Allmaras turbulence model 8 with compressibility corrections 9 and an approach for tripping the boundary layer at discrete locations. In general, the comparison between the simulations and flight data is remarkably good. ADD DETAILS...

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Section: Introductionmentioning

confidence: 99%

Hypersonic Navier Stokes Comparisons to Orbiter Flight Data

Candler¹,

Campbell

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Instability and transition mechanisms induced by skewed roughness elements in a high-speed laminar boundary layer

Groskopf

Kloker

2016

J. Fluid Mech.

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The disturbance evolution in a Mach-4.8 zero-pressure-gradient flat-plate boundary-layer flow altered by discrete three-dimensional roughness elements is investigated including a laminar breakdown scenario. Direct numerical simulation (DNS), as well as the biglobal linear stability theory based on two-dimensional eigenfunctions in flow cross-sections, are applied. Roughness elements with high ratios of spanwise width to streamwise length are compared at varying height and skewing angles with respect to the oncoming flow. For an oblique roughness, the element’s height is varied between 27 % and 68 % of the undisturbed boundary-layer thickness. Compared to a symmetric roughness element an obliquely placed element generates a more pronounced low-speed streak in the roughness wake. The linear stability analysis reveals the occurrence of eigenmodes that can be associated with the first and second modes in the flat-plate flow. At identical roughness height, larger amplification is found for the eigenmodes of the oblique set-up. The results are confirmed by unsteady DNS showing very good agreement with stability theory; transient-growth behaviour in the near wake of the roughness is of minor importance. The comparison of the results gained for adiabatic wind-tunnel flow conditions with those for atmospheric-flight conditions with wall cooling reveals significant differences in the wake vortex system with subsequent impact on the stability properties of the flow. The hot-flow cases are less unstable at identical roughness Reynolds numbers. A variation of the wall cooling shows that the roughness-wake first- and second-mode behaviour is similar to that of the flat-plate flow: wall cooling stabilizes the first-mode and destabilizes the second-mode instabilities of the roughness wake.

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