BUFFET RESPONSE AND AERODYNAMIC DAMPING CHARACTERISTICS OF AEROELASTICALLY SCALED TITAN III/MOL CONFIGURATIONS AT TRANSONIC SPEEDS
Abstract
A wind tunnel investigation was conducted to obtain the buffet response and aerodynamic damping of 0.07-scaled aeroelastic models of Titan III/ MOL configurations at transonic Mach numbers. Buffet response results were obtained in the form of bending moments at a selected model station. Aerodynamic damping results were obtained by the forced-oscillation technique, whereby the elastic modes of the model were excited by an electromagnetic shaker, and the exciting force and resulting model acceleration were recorded. A phase separation technique was used to resolve the structural damping (air-off conditions) and combined structural and aerodynamic damping (air-on conditions) from the measured force and acceleration. The test was conducted in the Mach number range from 0.80 to 1.10 and at zero angle of attack. All configurations experienced peak buffet response near Mach number 0.95. The buffet response for the Gemini and SV-5 configurations agreed reasonably well with previous test results for the same or similar configurations. The aerodynamic damping was generally positive and varied with Mach number. The largest variations occurred in the Mach number range from 0.925 to 1.00 for the Gemini and SV-5 configurations. Increasing dynamic pressure caused an increase in aerodynamic damping, although the increase in damping was not necessarily proportional to dynamic pressure.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1967
- Accession Number
- AD0820218
Entities
People
- J. E. Robertson
- T. R. Brice
Organizations
- Arnold Engineering Development Complex