Simulation of realistic rotor blade-vortex interactions using a finite-difference techniqueA numerical finite-difference code has been used to predict helicopter blade loads during realistic self-generated three-dimensional blade-vortex interactions. The velocity field is determined via a nonlinear superposition of the rotor flowfield. Data obtained from a lifting-line helicopter/rotor trim code are used to determine the instantaneous position of the interaction vortex elements with respect to the blade. Data obtained for three rotor advance ratios show a reasonable correlation with wind tunnel data.
Document ID
19890054704
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hassan, Ahmed A. (McDonnell-Douglas Helicopter Co. Mesa, AZ, United States)
Charles, Bruce D. (McDonnell Douglas Helicopter Co. Mesa, AZ, United States)