26th AIAA Applied Aerodynamics Conference 2008
DOI: 10.2514/6.2008-6921
|View full text |Cite
|
Sign up to set email alerts
|

Wing Deformation Measurements of the DLR-F6 Transport Configuration in the National Transonic Facility (Invited)

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
5

Citation Types

0
5
0

Year Published

2011
2011
2023
2023

Publication Types

Select...
8
1

Relationship

0
9

Authors

Journals

citations
Cited by 16 publications
(5 citation statements)
references
References 5 publications
0
5
0
Order By: Relevance
“…Surface visualization techniques have found varying degrees of success to date in high pressure, cryogenic wind tunnels. Temperature sensitive paint [6,7], Moiré interferometry [8], and photogrammetry [9] have been used successfully for qualitative and quantitative flow and aerodynamic surface measurements, while the pressure sensitive paint technique has only achieved limited qualitative success [10][11][12], though modern signal-lifetime-based variants have shown more promise [12]. Techniques sensitive to density, such as shadowgraphy, schlieren, and variants [14,15] as well as Rayleigh scattering [16][17][18], have shown some utility at qualitative and quantitative off-body measurements.…”
Section: Introductionmentioning
confidence: 99%
“…Surface visualization techniques have found varying degrees of success to date in high pressure, cryogenic wind tunnels. Temperature sensitive paint [6,7], Moiré interferometry [8], and photogrammetry [9] have been used successfully for qualitative and quantitative flow and aerodynamic surface measurements, while the pressure sensitive paint technique has only achieved limited qualitative success [10][11][12], though modern signal-lifetime-based variants have shown more promise [12]. Techniques sensitive to density, such as shadowgraphy, schlieren, and variants [14,15] as well as Rayleigh scattering [16][17][18], have shown some utility at qualitative and quantitative off-body measurements.…”
Section: Introductionmentioning
confidence: 99%
“…Despite the significant challenges associated with testing in high-pressure, cryogenic wind tunnels, several diagnostics have found use in TCTs, albeit to varying levels of success. Measurement techniques such as photogrammetry [5,6] and Moiré interferometry [7] have been successfully applied in the National Transonic Facility (NTF) and the European Transonic Windtunnel (ETW) to provide aeroelastic deformation measurements on a variety of different models. On-body surface pressures and temperatures have been measured using cryogenic pressure-and temperature-sensitive paints [8][9][10][11][12].…”
Section: Introductionmentioning
confidence: 99%
“…The induced wing section torsion will decrease the local angle of attack to which the aerodynamic force is extremely sensitive. In the transonic wind tunnel test of the DLR-F6 model, a configuration designed and tested by Deutschen Zentrums für Luft-und Raumfahrt (DLR), the wing tip torsion is up to −0.4 • at low flow dynamic pressure [5]. In addition, the decrease in drag coefficient caused by model deformation is up to 10 drag counts [6].…”
Section: Introductionmentioning
confidence: 99%