Design Criteris for the Predition and Prevention of Panel Flutter. Volume I: Criteria Presentation

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Report Number: AFFDL TR 67-140
Author(s): Lemley, Clark E.
Corporate Author(s): McDonnell Douglas Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1968-08
Pages: 60
Contract: AF 33(615)-5295
DoD Project: 1370
DoD Task: 137003
Identifier: AD0840581

The program described in this report was performed to bring together all available data from wind tunnel test, flight test, vibration test, thermal test and theoretical investigations to form comprehensive panel flutter design criteria. Procedures were developed which are applicable to the environment and various panel structural arrangements for transonic, supersonic, and hypersonic aircraft; aerospace re-entry vehicles, and boosters. This report (Volume I) presents a set of criteria for the design of flutter-free panels. The design procedure provides for initially establishing the required thickness at neutral stability of a flat, unstressed, unswept panel. Thickness corrections are then made to account for various parameters that are known to affect panel flutter boundaries.

Provenance: Lockheed Martin Missiles & Fire Control

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