Flutter Model Tests Of A Swept-back, All-moving Horizontal Tail At Supersonic Speeds

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Report Number: WADC TR 56-285
Author(s): Asher, Gifford W.
Corporate Author(s): Massachusetts Inst Of Tech Cambridge
Laboratory: Aircraft Laboratory
Date of Publication: 1957-11
Pages: 64
Contract: AF 33(616)-2751
DoD Project: 1370
DoD Task: 13479
Identifier: AD0142088

This report describes the flutter testing at supersonic speeds of a series of swept-back all-moving stabilizers. An attempt was made to define the flutter boundaries, for one location of the pitching axis, over the Mach number range of 1.3 to 2.1, by testing at a number of different levels of stabilizer stiffness, and at a number of different pitching frequencies. The results indicate that large increases in the region of instability can occur due to the introduction of the pitching degrees of freedom. The test results follow the trends of theoretical calculations, but the quantitative correlation between the theoretical and the experimental results is only fair.

Provenance: Lockheed Martin Missiles & Fire Control

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