2016
DOI: 10.1177/1475472x16659384
|View full text |Cite
|
Sign up to set email alerts
|

Time-resolved PIV measurements of a tip leakage flow

Abstract: International audienceno abstrac

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
1
1
1
1

Citation Types

0
23
0

Year Published

2016
2016
2022
2022

Publication Types

Select...
7

Relationship

2
5

Authors

Journals

citations
Cited by 19 publications
(23 citation statements)
references
References 8 publications
0
23
0
Order By: Relevance
“…It progressively deviates from the suction surface and its vorticity diffuses, confirming a trend evidenced in the experiment. 7 High levels of vorticity are also observed in the leakage flow below the airfoil.
Figure 6.Contours of non-dimensional mean axial vorticity on four cross-stream planes near the trailing edge of the airfoil.
…”
Section: Resultsmentioning
confidence: 98%
See 1 more Smart Citation
“…It progressively deviates from the suction surface and its vorticity diffuses, confirming a trend evidenced in the experiment. 7 High levels of vorticity are also observed in the leakage flow below the airfoil.
Figure 6.Contours of non-dimensional mean axial vorticity on four cross-stream planes near the trailing edge of the airfoil.
…”
Section: Resultsmentioning
confidence: 98%
“…Various experimental results are available on this configuration, as reported in the companion paper by Jacob et al. 7 The blade chord–length is c = 0.2 m. In the present numerical study, the following conditions are selected: U 0 = 70 m/s and h = 0.01 m. The chord-based Reynolds number is about 9.3 × 10 5 , and the Mach number is 0.2.
Figure 1.Sketch of the configuration.
…”
Section: Simulation Set-upmentioning
confidence: 99%
“…In both the experiment [6,7] and the simulation [8,9], a broad hump was observed in near-field spectra at the airfoil tip, around 1.3 kHz. Moreover, its frequency range, which extends over more than two octave bands, is located within that of the tip-leakage noise (0.7-7 kHz), which makes it particularly interesting.…”
Section: Wavelet Analysis: Methodologymentioning
confidence: 88%
“…In a previous version of the experiment [10], the angle of attack was 15 deg (0.5 deg), but the experimental results used in the present paper have been obtained during a more recent campaign, in which the angle of attack had to be set to 16.5 deg (0.5 deg) in order to recover the same airfoil loading as the original experiment. The details of the experimental configuration and an analysis of the experimental results are presented by Jacob et al [6,7].…”
Section: A Experimental Configurationmentioning
confidence: 99%
See 1 more Smart Citation