Abstract
The measured response of an airplane fuselage structure to turbulent boundary layer excitation is presented for two locations on the fuselage and three flight Mach numbers. At certain flight conditions and structural locations the vibration field shows broadband convection in the downstream direction, but at other locations and flight conditions the progressive wave system is replaced by standing waves. The presence of broadband convection can be related to the occurrence of aerodynamic coincidence, which is associated with high correlation in broad and narrow frequency bands. In the circumferential direction the vibration correlation is much lower than that in the flow direction, the correlation between adjacent panels being essentially zero.
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