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A Method Of Characteristics Approach To The Problem Of Supersonic Flow Past Oscillating Cascades With Finite Blade Thickness
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Book Synopsis A Method of Characteristics Approach to the Problem of Supersonic Flow Past Oscillating Cascades with Finite Blade Thickness by : Konrad Vogeler
Download or read book A Method of Characteristics Approach to the Problem of Supersonic Flow Past Oscillating Cascades with Finite Blade Thickness written by Konrad Vogeler and published by . This book was released on 1978 with total page 163 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of characteristics approach is described for the computation of supersonic flow past oscillating cascades having blades of finite thickness distribution. The transonic small disturbance equation is solved for cascades with subsonic leading-edge locus. Sample calculations are presented for the inlet and passage flow and comparisons are given with calculations for flat-plate cascades and available measured pressure distributions. (Author).
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 812 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of Supersonic Flow Past Oscillating Cascades Using Linear and Nonlinear Methods by : Joseph Anthony Strada
Download or read book Analysis of Supersonic Flow Past Oscillating Cascades Using Linear and Nonlinear Methods written by Joseph Anthony Strada and published by . This book was released on 1977 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study presents two methods of analysis for the supersonic oscillating cascade with subsonic leading edge. A relatively straightforward solution is developed for the slowly oscillating finite and infinite flat-plate cascades which provides simple analytical expressions for the unsteady pressure distributions. Comparison with other solutions is generally excellent. Some additional linear topics including resonance and a unique inflow condition are also treated. In addition a nonlinear method of charcteristics solution for finite cascades is described which permits analysis of blade thickness effects on flutter. At this time, only the inlet and passage flow computations have been completed and are compared with available experimental data. (Author).
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 836 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development Publisher : ISBN 13 : Total Pages :644 pages Book Rating :4.3/5 (243 download)
Book Synopsis AGARD Conference Proceedings by : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
Download or read book AGARD Conference Proceedings written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development and published by . This book was released on 1978 with total page 644 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness by : Maurice Holt
Download or read book Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness written by Maurice Holt and published by . This book was released on 1960 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flat Plate Cascades at Supersonic Speed by : Rashad M. El Badrawy
Download or read book Flat Plate Cascades at Supersonic Speed written by Rashad M. El Badrawy and published by . This book was released on 1956 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: A brief review of exact two-dimensional supersonic flow theory and Ackeret's linearized theory are first presented. The lift and drag coefficients of a cascade of flat plates are calculated exactly and compared to those obtained using the linearized theory. The forces on the cascade are determined for unsteady inlet flow. The flat plate cascade theory is extended to compute the efficiency of a supersonic propeller with friction and finite blade thickness.
Book Synopsis Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness by : Maurice Holt
Download or read book Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness written by Maurice Holt and published by . This book was released on 1960 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this case the whole disturbed flow field also varies sinusoidally with span. In region (i) the pressure satisfies the telegraph equation and the problem of calculating the disturbed flow field reduces to an integro-differential-difference equation for the distorted shock shape function. The solution of this equation, the existence and uniqueness of which is established, is obtained in the form of series expansions in chordwise distance on the shock ... In region (ii) the surface pressure satisfies a Volterra integral equation which can be solved by a simple numerical procedure. The present paper takes no account of edge effects, which must be treated separately as a conefield problem.
Download or read book The Shock and Vibration Digest written by and published by . This book was released on 1974 with total page 656 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book AIAA Bulletin written by and published by . This book was released on 1974 with total page 800 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Use of a Characteristic Surfaces for Unsymmetrical Supersonic Flow Problems by : Wolfgang E. Moeckel
Download or read book Use of a Characteristic Surfaces for Unsymmetrical Supersonic Flow Problems written by Wolfgang E. Moeckel and published by . This book was released on 1949 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Application of the method of characteristics to the linearized three-dimensional equation results in a relatively simple system of difference equations that can be used to compute the supersonic flow past boundaries for which no other linearized solutions are available.
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1965 with total page 568 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1971 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Book Synopsis Government Reports Annual Index by :
Download or read book Government Reports Annual Index written by and published by . This book was released on 1991 with total page 1654 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Theoretical Investigation of the Flutter Characteristics of Supersonic Cascades with Subsonic Leading-Edge Locus by : James Keith Bell
Download or read book Theoretical Investigation of the Flutter Characteristics of Supersonic Cascades with Subsonic Leading-Edge Locus written by James Keith Bell and published by . This book was released on 1975 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt: Supersonic flow past a semi-infinite array of flat plate cascaded airfoils is analyzed using a linearized method of characteristics procedure. For a cascade having subsonic leading-edge locus, but otherwise arbitrary geometry, frequency of blade oscillation, and interblade phase angle, pressure distributions and lift forces and moments are determined. These are used for flutter analysis and the determination of flutter boundaries. In addition, the linearized method of characteristics procedure is used to analyze supersonic flow through cylindrical shells. Pressure distributions and generalized forces are computed for arbitrary radius-to-length ratios, axial and circumferential mode numbers, and frequency of panel oscillation. (Author).
Download or read book NASA SP. written by and published by . This book was released on 1991 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1994 with total page 898 pages. Available in PDF, EPUB and Kindle. Book excerpt:
