Klein, Christian and Konrath, Robert and Beck, Walter (2006) Aerodynamic measurement technology. AIAA – Aerospace America, December 2006, p. 22. Aerospace Measurement Technology TC contribution.
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For the International Vortex Flow Experiment 2 (VFE-2) wind tunnel tests were carried out from the German Aerospace Center (DLR) on a 65° delta wing at sub- and transonic speeds for which the model was provided from NASA Langeley. Pressure distributions on the model surface were determined using the Pressure Sensitive Paint (PSP) technique. From these results test cases were selected for Particle Image Velocimetry (PIV) measurements to get details of the flow field. Above the delta wing with rounded leading edges a vortex system consisting of an inner and outer primary vortex could be detected and visualized, which is subject of discussion of the VFE-2 group.
|Additional Information:||Article / Aerospace Sciences|
|Title:||Aerodynamic measurement technology|
|Journal or Publication Title:||AIAA – Aerospace America|
|In ISI Web of Science:||No|
|Page Range:||p. 22|
|Publisher:||Aerospace Measurement Technology TC contribution|
|Series Name:||AIAA Aerospace America - The Year in Review 2006|
|Keywords:||Pressure Sensitive Paint (PSP), Particle Image Velocimetry (PIV), Vortex Flow Experiment|
|HGF - Research field:||Aeronautics, Space and Transport (old)|
|HGF - Program:||Aeronautics|
|HGF - Program Themes:||Aircraft Research|
|DLR - Research area:||Aeronautics|
|DLR - Program:||L AR - Aircraft Research|
|DLR - Research theme (Project):||L - Flight Physics|
|Institutes and Institutions:||Institute of Aerodynamics and Flow Technology > Experimental Methods|
|Deposited By:||Ilka Micknaus|
|Deposited On:||06 Mar 2007|
|Last Modified:||27 Apr 2009 13:14|
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