Determination of Metal Life for New Nickel Alloy ÉP800-VD Rotor Blades

Kazanskii, D. A.; Gladshtein, V. I.

doi:10.1007/s10749-013-0442-1

Cited by 2 publications

(4 citation statements)

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“…The present work continues the previous studies published in [13][14][15][16]. When we visualized a flow using the PIV method, we indicated that the flow is attached to the model for 14 s, when the discharge is turned on, described and illustrated the stages of the flow recon struction from the undisturbed state into the disturbed one at an interval of 0.5 ms.…”

Section: Introductionsupporting

confidence: 86%

“…Note that the effect of discharge on the airfoil model aerodynamic characteristics becomes close to the effect on the corresponding characteristics of bluff bodies (cylinder, cone, and plate perpendicular to flow). Nevertheless, the frequency ranges of HF dis charge modulation were not revealed using the airfoil model at which the aerodynamic drag would increase considerably, as was shown for the cylinder model [16,18].…”

Section: Discussion Of Experimental Resultsmentioning

confidence: 94%

“…It was indicated in [16] that the flow separation point shifts by one third of the wing chord length over about 14 ms, when the modulation frequency and power (W) are 130 Hz and 400 W, respectively. The parametric studies of the modulation frequency effect on the aerodynamic characteristics of the airfoil model con firm these data.…”

Section: Discussion Of Experimental Resultsmentioning

confidence: 99%

“…In several works [10][11][12][13][14][15][16], the airfoil leading edge separation at small Reynolds numbers was controlled by different DBD types. It is assumed that discharge can be a pulse source in the boundary layer and a tur bulizer in this configuration.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic quality management for the NACA 23012 airfoil model using the surface high-frequency discharge

et al. 2014

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The effect of the surface capacity HF discharge on airfoil flow around has been studied in the sit uation when the oncoming flow velocity is 20 m/s and the Reynolds numbers are Re = 10 5 . The power deliv ered to discharge was modulated with a frequency of 3 × 10 2 -2 × 10 4 Hz, which corresponds to a Strouhal number of St = 1.2-80, and the average electric power (W av ) was 50-400 W. It has been indicated that the aerodynamic drag decreased and the lift increased at stall and post stall angles of attack when the HF dielec tric barrier discharge was turned on. A nonstationary stochastic change in the C x and C y aerodynamic char acteristics was observed at a stall angle in the St = 4-10 range of Strouhal numbers when the power was insuf ficient (W av ≈ 100 W).

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Section: Introductionsupporting

confidence: 86%

Section: Discussion Of Experimental Resultsmentioning

confidence: 94%

Section: Discussion Of Experimental Resultsmentioning

confidence: 99%