The numerical simulations were carried out for the study of trailing-edge lateral blowing for the delta wing. The blowing decreases the pressure on the upper surface and increases the pressure on the lower surface, but the effect is somewhat different at each angle of attack. At low angles of attack, the blowing modifies the pressure only in the potential flow region. At moderately high angles of attack, the induced lower pressure affects the leading-edge separation vortex over the wing. The vortex is strengthened by the blowing. At higher angles of attack where the vortex breakdown occurs, the blowing helps the leading-edge separation vortex to recover. The breakdown is delayed. The blowing increases both the lift and drag, but the increase of the lift is much larger than that of the drag. Therefore, the blowing improves the lift/drag ratio.
Enhancement of the leading-edge separation vortices by trailing-edge lateral blowing
Verstärkung der Wirbelablösung an der Flügeleintrittskante durch Queranblasen an der Hinterkante des Deltaflügels
AIAA Journal ; 34 , 9 ; 1943-1945
1996
3 Seiten, 4 Bilder, 10 Quellen
Aufsatz (Zeitschrift)
Englisch
Enhancement of the Leading-Edge Separation Vortices by Trailing-Edge Lateral Blowing (TN)
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