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Proceedings Paper

PIV measurements of unsteady transonic flow fields above a NACA 0012 airfoil
Author(s): Markus Raffel; Juergen Kompenhans
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Paper Abstract

The instantaneous flow field above a NACA 0012 airfoil has been investigated by means of Particle Image Velocimetry (PIV). Two different flow conditions were realized in the high speed blow down wind tunnel of DLR Gottingen in order to obtain a flow field similar to that above a rotor blade of a helicopter. In the first part of the experiment the angle of incidence varied from (alpha) equals 5 degree(s) to (alpha) equals 20 degree(s) at a freestream velocity of Ma equals 0.25 in order to simulate the flow above the retreating blade of the rotor. Typical values for the second measuring sequence were (alpha) equals 0 degree(s) to (alpha) equals 5 degree(s) and Ma equals 0.75 (advancing blade). Due to some technical improvements of the DLR PIV-System, such as a high speed rotating mirror system and an optimized seeding device, it was possible to obtain the velocity data of these instantaneous flow fields with an accuracy high enough to allow a later comparison with data of numerical calculations.

Paper Details

Date Published: 6 August 1993
PDF: 8 pages
Proc. SPIE 2052, Fifth International Conference on Laser Anemometry: Advances and Applications, (6 August 1993); doi: 10.1117/12.150547
Show Author Affiliations
Markus Raffel, DLR (Germany)
Juergen Kompenhans, DLR (Germany)


Published in SPIE Proceedings Vol. 2052:
Fifth International Conference on Laser Anemometry: Advances and Applications

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