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Dynamic stall modeling and correlation with experimental data on airfoils and rotorsTwo methods for modeling dynamic stall have been developed. The alpha, A, B method generates lift and pitching moments as functions of angle of attack and its first two time derivatives. The coefficients are derived from experimental data for oscillating airfoils. The Time Delay Method generates the coefficients from steady state airfoil characteristics and an associated time delay in stall beyond the steady state stall angle. Correlation with three types of test data shows that the alpha, A, B method is somewhat better for use in predicting helicopter rotor response in forward flight. Correlation with lift and moment hysteresis loops generated for oscillating airfoils was good for both models.
Document ID
19740026378
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Carlson, R. G.
(United Aircraft Corp. Stratford, CT, United States)
Blackwell, R. H.
(United Aircraft Corp. Stratford, CT, United States)
Commerford, G. L.
(United Aircraft Corp. Stratford, CT, United States)
Mirick, P. H.
(Army Air Mobility R and D Lab. Fort Eustis, Va., United States)
Date Acquired
August 7, 2013
Publication Date
January 1, 1974
Publication Information
Publication: NASA. Ames Res. Center Rotorcraft Dyn.
Subject Category
Aircraft
Accession Number
74N34491
Funding Number(s)
CONTRACT_GRANT: DAAJ02-72-C-0105
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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