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Correlation of Puma airloads: 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 helicopter 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
19890019127
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Strawn, Roger C. (NASA Ames Research Center Moffett Field, CA, United States)
Desopper, Andre (NASA Ames Research Center Moffett Field, CA, United States)
Miller, Judith (NASA Ames Research Center Moffett Field, CA, United States)
Jones, Alan (Royal Aerospace Establishment Farnborough, United Kingdom)
Date Acquired
September 6, 2013
Publication Date
August 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:102226
NASA-TM-102226
A-89223
USAAVSCOM-TM-89-A-001
Accession Number
89N28498
Funding Number(s)
PROJECT: RTOP 992-21-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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