Investigation of the Aeroelastic Stability of Thin Cylindrical Shells at Subsonic Mach Numbers.

摘要

Boundary-layer and static-pressure data were obtained over a rigid pressure shell at Mach numbers from 0.6to 0.9and Reynolds numbers per foot from 300,000to 5,300,000. These data were obtained with and without the addition of air injected into the boundary layer through a circular slot upstream of the test shell. Static aeroelastic characteristics of thin cylindrical shells were obtained at Mach number 0.9without the use of boundary-layer control and without shell axial-force loading. An aeroelastic buckling failure was induced on all three shells by reducing the cavity pressure. Flutter of the shell was not encountered during the test. (Author)