The principle of aeroelastic tailoring with advanced composite materials to increase the divergence speed of a forward swept wing has been demonstrated through low speed wind tunnel tests. The approach was to perform a low cost, fairly simple wind tunnel test on a variable sweep cantilever wing model. Available analytical methods were used and were shown to accurately predict the divergence speed of both aluminum and composite plate structures in the subsonic speed range. Methods were evaluated for predicting the onset of divergence using subcritical wind tunnel data. Results of the analyses and tests are presented. (Author)
Demonstration of the Principle of Aeroelastic Tailoring Applied to Forward Swept Wings
1982
126 pages
Report
Keine Angabe
Englisch
Aircraft , Sweptforward wings , Composite materials , Aeroelasticity , Variable sweep wings , Graphite , Epoxy composites , Structural properties , Composite structures , Aluminum , Bending stress , Dynamic pressure , Static pressure , Stiffness , Stress analysis , Damping , Rotation , Coefficients , Mathematical prediction , Angle of attack , Plates , Aircraft panels , Low velocity , Wind tunnel tests , Aeroelastic tailoring , Cantilever wings , S/L change 8412
Aeroelastic Tailoring of Forward Swept Composite Wings
AIAA | 1981
|Aeroelastic tailoring of forward swept composite wings
AIAA | 1980
|