Microblowing for High-Angle-of-Attack Vortex Flow Control on a Fighter Aircraft

2001 ◽  
Vol 38 (3) ◽  
pp. 454-457 ◽  
Author(s):  
Frederick W. Roos
Keyword(s):  
Flow Control ◽  
Vortex Flow ◽  
Angle Of Attack ◽  
High Angle ◽  
High Angle Of Attack ◽  
Fighter Aircraft

Numerical Simulations of Closed-Loop Flow Control of a Tangent Ogive at a High Angle of Attack

2013 ◽  
Author(s):  
Christopher O. Porter ◽  
Casey P. Fagley ◽  
John A. Farnsworth ◽  
Jurgen Seidel ◽  
Thomas E. McLaughlin
Keyword(s):  
Flow Control ◽  
Numerical Simulations ◽  
Closed Loop ◽  
Angle Of Attack ◽  
High Angle ◽  
High Angle Of Attack

FLOW CONTROL AND MECHANISM FOR SLENDER BODY AT HIGH ANGLE OF ATTACK

2005 ◽  
Vol 19 (28n29) ◽  
pp. 1571-1574 ◽  
Author(s):  
XIAO MING ◽  
YUNSONG GU
Keyword(s):  
Flow Control ◽  
High Frequency ◽  
Angle Of Attack ◽  
Control Technique ◽  
High Angle ◽  
Dynamic Measurements ◽  
Wind Tunnel Experiments ◽  
Rolling Angle ◽  
High Angle Of Attack ◽  
Side Force

The wind tunnel experiments for high angle of attack aerodynamics were designed from the inspiration of understanding the mechanism and development of an innovative flow control technique. The side force, varying with the different rolling angle, is featured by bi-stable situation, and can be easily switched by a tiny disturbance. A miniature strake is attached to the nose tip of the model. When the strake is stationary, the direction of the side force can be controlled. When the nose tip strake, as an unsteady control means, is swung the flow pattern could be controlled. The results obtained from dynamic measurements of section side force indicate that when the strake swing at lower frequency the side force can follow the cadence of the swinging strake. With increasing frequency, the magnitude of the side force decreases. At still high frequency, the side force diminishes to zero. The side forces could be also changed proportionally. Based on the experimental factors, the mechanism of the asymmetry is discussed.

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