The results of experiments in which an unsteady separating flow was generated on the surface of an airfoil immersed in a subsonic wind tunnel freestream are discussed. An investigation of the global ensemble averaged vorticity field generated by oscillations of a fence-type spoiler located on one surface of the airfoil has confirmed the presence of a dynamically evolving vortex-like structure bearing a strong resemblance to the one encountered in classical dynamic stall. The growth and development of the shear layer region is characterized through iso-vorticity contour maps at select phase points during the motion cycle. A detailed description of flow field behavior is provided for several values of the dimensionless spoiler frequency and freestream Reynolds number. The correlation of these results with corresponding surface pressure measurements is also presented. (Kursetz)
Aerodynamic characteristics of an unsteady separated flow
Aerodynamische Charakteristik einer ungleichmaessigen Grenzschichtstroemung
AIAA-Papers ; Jan ; 1-13
1979
13 Seiten, 14 Bilder, 21 Quellen
Aufsatz (Konferenz)
Englisch
Separated flow unsteady aerodynamic theory
AIAA | 1985
|DOAJ | 2017
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