DEVELOPMENT, ANALYSIS, AND TESTING OF CANTILEVERED 6%-THICK 70 DEGREE DELTA WING FLUTTER MODELS. PART II. TRANSONIC TESTS
Abstract
A series of 6%-thick 70 degree delta wing cantilevered flutter models was designed, built, and flutter-tested at Mach numbers 0.85, 0.855, 0.90, 0.95, 1.00, 1.03, 1.05, and 1.08. The models tested have a sandwich structure comprised of an aluminum insert of 0.100-in. thickness surrounded with a plastic foam of negligible weight and stiffness. This structure provides the desired aerodynamic contour and yet possesses a stiffness low enough to permit flutter in the wind tunnel. The flutter dynamic pressures and frequencies obtained were lower than those predicted by using experimental aerodynamic influence coefficients. The unsteady effects, as determined by the NASA Kernel Function, when included in the predictions based on the experimentally determined steady aerodynamic influence coefficients, apparently increase the predicted flutter dynamic pressure slightly and decrease the flutter frequency by about 20%. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1964
- Accession Number
- AD0356026
Entities
People
- Bernard Mazelsky
- Harry B. Amey Jr.
- Patrick J. Cunningham
Organizations
- Aerojet Rocketdyne Holdings