Aeroelastic Problems of Low Aspect Ratio Wings

Abstract

This final paper of the series deals with the application of the structural and aerodynamic matrices to determine the final steady state loading on the wing, with a view to the requirements of the stress analyst. It is also shown how the stability derivatives of the elastic wing may be obtained, if a system of unit loads is employed in the calculations. Finally the occurrence of wing divergence and control surface reversal speeds are discussed in the light of the proposed methods.