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Numerical analysis of supersonic flow through oscillating cascade sections by using a deforming gridA finite difference code was developed for modeling inviscid, unsteady supersonic flow by solution of the compressible Euler equations. The code uses a deforming grid technique to capture the motion of the airfoils and can model oscillating cascades with any arbitrary interblade phase angle. A flat plate cascade is analyzed, and results are compared with results from a small-perturbation theory. The results show very good agreement for both the unsteady pressure distributions and the integrated force predictions. The reason for using the numerical Euler code over a small-perturbation theory is the ability to model real airfoils that have thickness and camber. Sample predictions are presented for a section of the rotor on a supersonic throughflow compressor designed at NASA Lewis Research Center. Preliminary results indicate that two-dimensional, flat plate analysis predicts conservative flutter boundaries.
Document ID
19890063439
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Huff, Dennis L.
(NASA Lewis Research Center Cleveland, OH, United States)
Reddy, T. S. R.
(Toledo, University OH, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 89-2805
Accession Number
89A50810
Distribution Limits
Public
Copyright
Other

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