A CALCULATION STUDY OF WING-AILERON FLUTTER IN TWO DEGREES OF FREEDOM FOR TWO-DIMENSIONAL SUPERSONIC FLOW
Abstract
Results are presented of some sample calculations made for the bending-aileron and torsion-aileron flutter of an idealized wing-aileron system (infinite aspect ratio, full-span aileron hinged at its leading edge) for several values of Mach number in supersonic flow and also for some subsonic Mach numbers. It is emphasized that the results are subject to various limitations and are not intended to be applicable to particular configurations. They may serve, however, to provide preliminary knowledge of the influence of variations in certain parameters and to indicate some of the differences in the trends exhibited by the calculations for high speeds and those trends known to exist for low speeds. The more influential parameters appear to be: mass balance of the control surface, control-surface frequency relative to wing frequency, and structural damping. An interesting result is the indication of an apparent reverse effect of mass balance at the transonic speeds for some wing-aileron configurations. A high value of control-surface frequency appears beneficial as does structure damping of the system. In several of the calculations, the possibility of flutter in a single degree of freedom is indicated.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1954
- Accession Number
- AD0029444
Entities
People
- Donald S. Woolston
- Vera Huckel
Organizations
- Langley Research Center