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Correlation of Puma airfoils - Evaluation of CFD prediction methodsA cooperative program was undertaken by research organizations in England, France, Australia and the U.S. to study the capabilities of computational fluid dynamics codes (CFD) to predict the aerodynamic loading on helicopter rotor blades. The program goal is to compare predictions with experimental data for flight tests of a research Puma helicopter with rectangular and swept tip blades. Two topics are studied. First, computed results from three CFD codes are compared for flight test cases where all three codes use the same partial inflow-angle boundary conditions. Second, one of the CFD codes (FPR) is iteratively coupled with the CAMRAD/JA heilcopter performance code. These results are compared with experimental data and with an uncoupled CAMRAD/JA solution. The influence of flow field unsteadiness is found to play an important role in the blade aerodynamics. Alternate boundary conditions are suggested in order to properly model this unsteadiness in the CFD codes.
Document ID
19900033990
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Strawn, Roger C.
(NASA Ames Research Center; U.S. Army, Aeroflightdynamics Directorate, Moffett Field CA, United States)
Desopper, Andre
(ONERA Chatillon-sous-Bagneux, France)
Miller, Judith
(NASA Ames Research Center Moffett Field, CA, United States)
Jones, Alan
(Royal Aerospace Establishment Farnborough, United Kingdom)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Publication Information
Publication: ONERA
Issue: 1989-
Subject Category
Aerodynamics
Report/Patent Number
ONERA, TP NO. 1989-185
Accession Number
90A21045
Distribution Limits
Public
Copyright
Other

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