A transonic flutter investigation was made of elastically and dynamically scaled models of the tee-tail of a patrol bomber. It was found that removal of the 15 degrees dihedral of the stabilizer used on the airplane raised the flutter boundary to higher dynamic pressures. The effect of Mach number on the flutter boundary was different for dihedral angles of 0 degrees and 15 degrees. The dynamic pressure at the flutter boundary increased approximately linearly with the torsional stiffness of the fin. Highspeed motion pictures indicated that the flutter mode consisted primarily of fin bending and fin torsion. (Author).

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