On basis of certain simplifying structural and aerodynamic assumptions, notably that wing bending and torsion occur along straight line, and strip theory, differential equations of equilibrium of swept elastic wing subjected to aerodynamic and inertial loads are formulated; formulas for lift and moment coefficients in terms of initial configuration and elastic deflections of wing given.
Formulation of aeroelastic problem for swept wing
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 16 , n 8
1949
14 pages
Bibliography
Article (Journal)
English
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