Transonic Noise Generation by Duct and Profile Flow.
Annual rept. no. 2, Apr 82-83,
MAX-PLANCK-INST FUER STROEMUNGSFORSCHUNG GOETTINGEN (GERMANY F R)
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To study the strong sound generation in the case of helicopter rotor vortex interaction, a vortex profile flow interaction experiment is performed in a transonic duct. Vortices are generated upstream of a NACA 0012 profile and the pressure and density fields are analyzed using digital signals processing methods and digital interferogram evaluation techniques. One of the current results is that a separation bubble is formed at the leading edge of the wing when the vortex passes over the profile. The complicated flow at the boundary of the profile seems to be one of the keys to the understanding of vortex profile interaction. Author