An experimental study of active control of fully separated flow over a symmetrical circular-arc airfoil at high angles of attack was performed. The experiments were carried out in a low-speed, open-circuit wind tunnel with the airfoil at angles of attack from 10 to 40 deg. Low-power input, unsteady excitation was applied to the leading or trailing edge. The actuation was provided by the periodic oscillation of a 4% chord flap placed on the suction side of the airfoil and facing the sharp edge. Pressure measurements over the airfoil show that flow control increased the normal force coefficient by up to 70%. The application of flow control on sharp-edged aircraft wings could lead to improved maneuverability, innovative flight control, and weight reduction.
Flow control of a sharp-edged airfoil
Beeinflussung der abgelösten Strömung um ein scharfkantiges Kreisbogenprofil
AIAA Journal ; 43 , 4 ; 716-726
2005
11 Seiten, 21 Bilder, 1 Tabelle, 16 Quellen
Aufsatz (Zeitschrift)
Englisch
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