Static aeroelasticity is examined for a wing with circulation control (CC) airfoils. The airfoils use tangential blowing over a rounded trailing edge to provide a lift augmentation proportional to the jet momentum of the blown air. Airfoil lift and pitching moment magnitudes are dependent on both angle of attack and jet momentum. In combination with an elastic structure, this double dependence of lift and moment lead to a CC reversal condition, which is analogous to aileron reversal. Increases in jet momentum beyond the reversal point result in lift decreases. Boundaries for torsional divergence and CC reversal are theoretically examined for the simple two-dimensional case and then for a three-dimensional wing. The wing analysis uses a modified lifting line theory and two-dimensional CC airfoil data to evaluate the behavior of a circulation control wing (CCW).
Aeroelastic Characteristics of a Circulation Control Wing
1976
136 pages
Report
Keine Angabe
Englisch
Aerodynamics , Fluid Mechanics , Aerodynamic control surfaces , Aeroelasticity , Lift , Airfoils , Wings , Stalling , Flutter , Blowers , Boundary layer control , Two dimensional , Three dimensional , Wind tunnel tests , Model tests , Theses , Static tests , Lift augmentation , Circulation controlled airfoils
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