Boundary-layer transition at supersonic speeds - Roughness effects with heat transfer.

Driest, E. R. Van; Blumer, C. B.

doi:10.2514/3.4551

Cited by 31 publications

(2 citation statements)

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“…The RANS computation predicts no flow separation for the 15 deg chamfered forward-facing step (10) and almost no pressure drag production; therefore, the drag level computed is very low, smaller than the 0.5 mm backward-facing step (1). The experiments exhibit flow separations for this geometry.…”

Section: Resultsmentioning

confidence: 92%

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Drag Induced by Flat-Plate Imperfections in Compressible Turbulent Flow Regimes

Molton

Hue

Bur

2015

Journal of Aircraft

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This paper presents the results of a coupled experimental and numerical study aimed at evaluating the influence of typical aircraft surface imperfections on the flat-plate drag production in fully turbulent conditions. A test campaign involving high-level measurement techniques, such as microdrag evaluation, near-wall laser Doppler veloeimetry, and oil-film interferometry, has been carried out at several Mach numbers from 0.5 to 1.3 to quantify the impact of a large range of flat-plate imperfections. Forward-facing and backw ard-facing plain and chamfered steps of different heights have been studied. A whole numerical study, based on Reynolds-averaged Navier-Stokes computations, has been completed and used for validation purposes. Given the very small order of magnitude of the forces to be measured and calculated, the relative comparison between experimental and numerical outcomes is satisfactory. Even if some local discrepancies exist, results show an overall good agreement in the positioning of the different imperfection drag productions. Such investigations are of prime interest to determine industrialization tolerances or excrescence geometries offering the best compromises between manufacturing costs and aerodynamic performances.freestream Mach number Palm = atmospheric pressure P, = stagnation pressure Re = freestream Reynolds number T; = stagnation temperature U = velocity U+ = normalized velocity Ur = friction velocity X = longitudinal coordinate z = vertical coordinate Z+ = normalized vertical coordinate < 5 = boundary-layer physical thickness V = kinematic viscosity Subscript O O -freestream state value

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Section: Resultsmentioning

confidence: 92%

“…Indeed, many publications deal with the impact of excrescences on the laminar-turbulent transition [1][2][3][4][5], but on the topic of drag penalty due to imperfections in fully turbulent conditions, the literature is not abundant. The current estimation methods are based on the use of tables, especially these available in Hoemer [6].…”

Section: Introductionmentioning

confidence: 99%