Aeroelastic effects on stabilizing fins were studied using experimentally determined flexibility coefficients; aerodynamic forces were estimated by means of second-order two-dimensional hybrid theory, taking wing tip Mach cone effect into account, for static analysis and by second-order piston theory for dynamic analysis; flutter boundaries based on first two natural modes of fins and body fundamental bending mode, were established and indicated freedom from flutter; comparison of results demonstrated influence of fin tip Mach cone effect and thickness effects in static analysis and importance of root attachment.
Aeroelastic investigation of three rocket fins at high mach numbers
Canada. Nat Research Council -- Aeronautical Report
1965
33 pages
Article (Journal)
English
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