FLUTTER DATA AT HYPERSONIC SPEEDS M=5 TO 10,
Abstract
A theoretical and experimental program was conducted in the Mach number range 5 less than or equal to M less than or equal to 10 to determine the effects of frequency ratio, Mach number, mass ratio, pitch damping and profile on the flutter characteristics of semirigid models having square planforms. Correlative flutter analyses were conducted for most of the configurations tested using piston theory aerodynamics. In addition, some analyses were conducted using experimentally measured values of the quasistatic piston theory aerodynamic coefficients. The major results of the investigation were: (1) The unpredicted destabilizing trend of the flutter velocity index previously noted in the Mach number range 6 less than or equal to M less than or equal to 8 is not caused by either the independent or combined effects of mass ratio and/or the structural damping coefficient in the pitch degree of freedom. (2) Regardless of the model parameters, or the Mach number at which the model was tested, an unpredicted limiting value of the frequency ratio was found below which flutter could not be obtained. (3) The limiting value of the frequency ratio below which flutter could not be obtained, appears to be a function of the center-of-gravity and the center-of-pressure position, but not of Mach number. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1963
- Accession Number
- AD0344434
Entities
People
- John C. Balcerak
- Richard P. White Jr.
Organizations
- Calspan