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S8 Engenharia Aeroespacial |
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Title:
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HIGH-LIFT SURFACES DEFLEXION FOR LOW-SPEED AIRFOIL
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Summary :
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ABSTRACT. THE RELATIVE ANGLES AND THE LEADING EDGE POSITIONS OF A SLAT AND A FLAP ARE OBTAINED IN ORDER TO MAXIMIZE THE LIFT COEFFICIENT OF A MULTI-ELEMENT AIRFOIL. THE FLOW OVER THIS COMPLEX CONFIGURATION IS CALCULATED THROUGH A VISCOUS-NON-VISCOUS INTERACTION PROCEDURE. THE POTENTIAL FLOW IS DETERMINED BY USING A PANEL METHOD BASED ON THE TANGENT DIPOLE AND ON THE VORTEX SINGULARITIES ASSOCIATED WITH THE STREAM FUNCTION, WHICH IS USED TO IMPOSE THE BOUNDARY CONDITION. THE BOUNDARY LAYER ON THE SURFACE OF EACH ELEMENT IS CALCULATED THROUGH A COMPUTATIONAL CODE BASED ON THE INTEGRAL EQUATIONS. SUCH CODE IS CAPABLE OF ANALYZING LAMINAR AND TURBULENT FLOWS AND FURNISHING THE FRICTION COEFFICIENT AND THE DISPLACEMENT THICKNESS, WHICH IS USED TO PERFORM THE VISCOUS-NON-VISCOUS COUPLING. TWO CASES ARE ANALYZED AND COMPARED: A THREE-ELEMENT AIRFOIL AND A FLAP-AIRFOIL CONFIGURATION.
KEY WORDS: POTENTIAL FLOW, BOUNDARY LAYER, OPTIMIZATION TECHNIQUE, THREE-ELEMENT AIRFOIL.
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Author :
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Girardi, Roberto da Motta
Paglione, Pedro 0
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Paper View :
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