Details
| Originalsprache | Englisch |
|---|---|
| Seiten (von - bis) | 233-240 |
| Seitenumfang | 8 |
| Fachzeitschrift | Experiments in fluids |
| Jahrgang | 43 |
| Ausgabenummer | 2-3 |
| Publikationsstatus | Veröffentlicht - 17 Juni 2007 |
| Extern publiziert | Ja |
Abstract
The compressible blade tip vortex of rotary wings has been the subject of numerous investigations and its importance for the understanding of the helicopter flow field has been clearly emphasised. Due to its great impact on the dynamics of the flow field, the investigation of the tip vortex is directly linked to issues of flow control and aeroacoustic optimisation. However, among velocity field data, additional core density information on the blade tip vortex is desirable with a view to vortex modelling. In this work we describe an airborne background oriented Schlieren system for full-scale helicopter flight tests as well as the first results of the tomographic reconstruction of the compressible vortex core. We report the measurements of both a 0.4 Mach-scaled rotor model of the MBB BO 105 and the corresponding full-scale helicopter in hover flight condition. The tomographic reconstruction of the data allows us to estimate the density and the radius for the viscous core.
ASJC Scopus Sachgebiete
- Ingenieurwesen (insg.)
- Numerische Mechanik
- Ingenieurwesen (insg.)
- Werkstoffmechanik
- Physik und Astronomie (insg.)
- Allgemeine Physik und Astronomie
- Chemische Verfahrenstechnik (insg.)
- Fließ- und Transferprozesse von Flüssigkeiten
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in: Experiments in fluids, Jahrgang 43, Nr. 2-3, 17.06.2007, S. 233-240.
Publikation: Beitrag in Fachzeitschrift › Artikel › Forschung › Peer-Review
}
TY - JOUR
T1 - Recent developments in background oriented Schlieren methods for rotor blade tip vortex measurements
AU - Kindler, Kolja
AU - Goldhahn, Erik
AU - Leopold, Friedrich
AU - Raffel, Markus
PY - 2007/6/17
Y1 - 2007/6/17
N2 - The compressible blade tip vortex of rotary wings has been the subject of numerous investigations and its importance for the understanding of the helicopter flow field has been clearly emphasised. Due to its great impact on the dynamics of the flow field, the investigation of the tip vortex is directly linked to issues of flow control and aeroacoustic optimisation. However, among velocity field data, additional core density information on the blade tip vortex is desirable with a view to vortex modelling. In this work we describe an airborne background oriented Schlieren system for full-scale helicopter flight tests as well as the first results of the tomographic reconstruction of the compressible vortex core. We report the measurements of both a 0.4 Mach-scaled rotor model of the MBB BO 105 and the corresponding full-scale helicopter in hover flight condition. The tomographic reconstruction of the data allows us to estimate the density and the radius for the viscous core.
AB - The compressible blade tip vortex of rotary wings has been the subject of numerous investigations and its importance for the understanding of the helicopter flow field has been clearly emphasised. Due to its great impact on the dynamics of the flow field, the investigation of the tip vortex is directly linked to issues of flow control and aeroacoustic optimisation. However, among velocity field data, additional core density information on the blade tip vortex is desirable with a view to vortex modelling. In this work we describe an airborne background oriented Schlieren system for full-scale helicopter flight tests as well as the first results of the tomographic reconstruction of the compressible vortex core. We report the measurements of both a 0.4 Mach-scaled rotor model of the MBB BO 105 and the corresponding full-scale helicopter in hover flight condition. The tomographic reconstruction of the data allows us to estimate the density and the radius for the viscous core.
UR - http://www.scopus.com/inward/record.url?scp=34548084624&partnerID=8YFLogxK
U2 - 10.1007/s00348-007-0328-9
DO - 10.1007/s00348-007-0328-9
M3 - Article
AN - SCOPUS:34548084624
VL - 43
SP - 233
EP - 240
JO - Experiments in fluids
JF - Experiments in fluids
SN - 0723-4864
IS - 2-3
ER -