NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
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)
Date Acquired
August 14, 2013
Publication Date
June 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 89-1847
Accession Number
89A42075
Funding Number(s)
CONTRACT_GRANT: NAS1-17145
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available