A MEASUREMENT OF THE STATIC AEROELASTIC DEFORMATION AND LOADING OF A WING IN SUPERSONIC FLOW.
Final rept. for Mar 61-Mar 63,
MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB
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The aeroelastic analysis of Zisfein, Donato and Farrell AD-155739 uses an aerodynamic matrix, a structural matrix and the initial angle of attack to predict the equilibrium pressures and shape of a wing. To test the accuracy of their methods, a flexible wing was built and instrumented with pressure taps and mirrors. The wing was tested at Mach numbers of 2 and 3, and both the pressure distribution and the deflected shape were measured. An aerodynamic matrix computed on the basis of the semiempirical procedures of the above authors was used to predict pressure distributions, and an experimentally determined structural matrix was used to find equilibrium angles of attack. Finally, these two matrices were used in the aeroelastic equations to compute pressures and angles of attack from the undeflected shape of the wing. Comparisons between theory and experiment are presented for eight different free stream conditions. Author