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Flutter Analysis Of A Supersonic Cascade In Time Domain Using An Adi Euler Solver
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Book Synopsis Flutter Analysis of Supersonic Axial Flow Cascades Using a High Resolution Euler Solver. Part 1: Formulation and Validation by :
Download or read book Flutter Analysis of Supersonic Axial Flow Cascades Using a High Resolution Euler Solver. Part 1: Formulation and Validation written by and published by . This book was released on 1992 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722244125 Total Pages :26 pages Book Rating :4.2/5 (441 download)
Book Synopsis Flutter Analysis of a Supersonic Cascade in Time Domain Using an Adi Euler Solver by : National Aeronautics and Space Administration (NASA)
Download or read book Flutter Analysis of a Supersonic Cascade in Time Domain Using an Adi Euler Solver written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-03 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aeroelastic stability of a two-dimensional cascade oscillating in supersonic axial flow is analyzed in the time domain. The aeroelastic model consists of a single degree of freedom typical section structural model for each blade of the cascade and an unsteady two-dimensional cascade aerodynamic model based on the Euler equations. The Euler equations are solved using a time accurate Alternating Direction Implicit (ADI) solution scheme. The aeroelastic equations are integrated in time. The effect of interblade phase angle is included in the aeroelastic analysis by an appropriate choice of initial and boundary conditions. Flutter predictions are obtained from the time response of a flat plate cascade in single degree of freedom pitching motion. The results correlate well with those obtained from a separate frequency domain flutter analysis for all values of interblade phase angles considered. Flutter results are then presented for cascades having airfoil sections representative of a supersonic throughflow fan. The validity of the time integration method for a cascade of airfoils at various interblade phase angles is demonstrated. Reddy, T. S. R. and Bakhle, M. A. and Huff, D. L. Glenn Research Center RTOP 535-03-01...
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Book Synopsis Aeronautical Enginnering: A Cumulative Index to a Continuing Bibliography (supplement 312) by :
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Book Synopsis Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines by : Kenneth C. Hall
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