An aeroelastic investigation of three rocket fins at high mach numbers

Report (1965)
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Published Date

31-12-1965

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Source:

National Research Council Aeronautical Report LR 477

Abstract

Aeroelastic effects on the stabilising fins of three high performance sounding rockets have been investigated at supersonic Mach numbers using experimentally determined flexibility coefficients . The aerodynamic farces have been estimated by means of a second - order two - dimensional hybrid theory , taking the wing tip Mach co ne effect into account, for the statie analysis and by second- order piston theory for the dynamic analysis. In the static analysis , the variation of fin lift and centre of pressure position has been determined as a function of the aerodynamic stiffness parameter. Comparison with wind tunnel data, available only for one of the fins analysed, showed good agreement. Flutter boundaries based on the first two natural modes of the fins (derived from the flexibility coefficients)

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