Prediction of blade-vortex interaction noise using airloads generated by a finite-difference techniqueThe present numerical finite-difference scheme for helicopter blade-load prediction during realistic, self-generated three-dimensional blade-vortex interactions (BVI) derives the velocity field through a nonlinear superposition of the rotor flow-field yielded by the full potential rotor flow solver RFS2 for BVI, on the one hand, over the rotational vortex flow field computed with the Biot-Savart law. Despite the accurate prediction of the acoustic waveforms, peak amplitudes are found to have been persistently underpredicted. The inclusion of BVI noise source in the acoustic analysis significantly improved the perceived noise level-corrected tone prediction.
Document ID
19910032602
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Tadghighi, Hormoz (McDonnell-Douglas Helicopter Co. Mesa, AZ, United States)
Hassan, Ahmed A. (McDonnell-Douglas Helicopter Co. Mesa, AZ, United States)
Charles, Bruce (McDonnell Douglas Helicopter Co. Mesa, AZ, United States)