Abstract
Recent flight tests of a Prop-Fan (advanced technology turboprop) model mounted on a business aircraft revealed noise levels on the fuselage surface considerably lower than was expected from theoretical calculations and other test experience. In this paper the role of the fuselage boundary layer in shielding the surface from noise via classical refraction effects is examined. In order to study the physical phenomenon with minimum mathematical complexity, the boundary layer is modeled by concentrating its shear in an infinitesimally thin layer displaced an effective boundary layer thickness from a rigid wall. Incident energy is assumed to arrive in plane waves. For the Prop-Fan model at its design cruise Mach number of 0·8, the theory indicates a strong shielding effect. The shielding diminishes at lower flight Mach number and for larger sound wavelengths. At full scale, the shielding effects will be less than in model scale because the wavelength of the dominant noise is larger relative to the fuselage boundary layer thickness.
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