An interactive boundary-layer procedure for oscillating airfoils including transition effects
An interactive boundary-layer procedure for oscillating airfoils including transition effects
- New search for: Cebeci, T.
- New search for: Carr, L.W.
- New search for: Jang, H.M.
- New search for: Cebeci, T.
- New search for: Carr, L.W.
- New search for: Jang, H.M.
An interactive boundary-layer method previously developed and tested for steady flows is used here in a quasi-steady manner to examine the evolution of the flow behavior around oscillating airfoils operating in light stall conditions. The calculations encompass the airfoil and wake flows at angles of attack which lead to flow separation. The location of the onset of transition is represented by a correlation based on steady flows. The results show the large effects of the viscous layer on the variation of lift coefficient with angle of attack and reduced frequency.
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An interactive boundary-layer procedure for oscillating airfoils including transition effects
Verfahren auf Basis der interaktiven Grenzschicht fuer oszillierende Tragfluegel unter Einschluss der Uebergangseffekte
AIAA-Papers ; Jan ; 1-7
1988
7 Seiten, 8 Bilder, 14 Quellen
Conference paper
English
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