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Analysis and test evaluation of the dynamic response and stability of three advanced turboprop models at low forward speedResults of wind tunnel tests at low forward speed for blade dynamic response and stability of three 62.2 cm (24.5 in) diameter models of the Prop-Fan, advanced turboprop, are presented. Measurements of dynamic response were made with the rotors mounted on an isolated nacelle, with varying tilt for nonuniform inflow. Low speed stall flutter tests were conducted at Mach numbers from 0.0 to 0.35. Measurements are compared to Eigen-solution flutter boundaries. Calculated 1P stress response agrees favorably with experiment. Predicted stall flutter boundaries correlate well with measured high stress regions. Stall flutter is significantly reduced by increased blade sweep. Susceptibility to stall flutter decreases rapidly with forward speed.
Document ID
19880004714
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Smith, Arthur F. (Hamilton Standard Windsor Locks, CT, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1985
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-175026
NAS 1.26:175026
HSER-11055
Accession Number
88N14096
Funding Number(s)
CONTRACT_GRANT: NAS3-22755
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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