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Airfoil wake and linear theory gust response including sub and superresonant flow conditionsThe unsteady aerodynamic gust response of a high solidity stator vane row is examined in terms of the fundamental gust modeling assumptions with particular attention given to the effects near an acoustic resonance. A series of experiments was performed with gusts generated by rotors comprised of perforated plates and airfoils. It is concluded that, for both the perforated plate and airfoil wake generated gusts, the unsteady pressure responses do not agree with the linear-theory gust predictions near an acoustic resonance. The effects of the acoustic resonance phenomena are clearly evident on the airfoil surface unsteady pressure responses. The transition of the measured lift coefficients across the acoustic resonance from the subresonant regime to the superresonant regime occurs in a simple linear fashion.
Document ID
19920066100
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Henderson, Gregory H.
(NASA Lewis Research Center Cleveland, OH, United States)
Fleeter, Sanford
(Purdue University West Lafayette, IN, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-3074
Accession Number
92A48724
Distribution Limits
Public
Copyright
Other

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