Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Analysis Of Supersonic Flow Past Oscillating Cascades Using Linear And Nonlinear Methods
Download Analysis Of Supersonic Flow Past Oscillating Cascades Using Linear And Nonlinear Methods full books in PDF, epub, and Kindle. Read online Analysis Of Supersonic Flow Past Oscillating Cascades Using Linear And Nonlinear Methods ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
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 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 0 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).
Book Synopsis Supersonic Flow Past Oscillating Airfoils Including Nonlinear Thickness Effects by : Milton D. Van Dyke
Download or read book Supersonic Flow Past Oscillating Airfoils Including Nonlinear Thickness Effects written by Milton D. Van Dyke and published by . This book was released on 1954 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: The analysis utilizes a smoothing technique which replaces the actual problem by one involving no kinked streamlines. This strategem eliminates all consideration of shock waves from the analysis, yet yields the correct solution for problems which actually contain shock waves.
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 1995 with total page 400 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Flow Past Oscillating Airfoils Including Nonlinear Thickness Effects by :
Download or read book Supersonic Flow Past Oscillating Airfoils Including Nonlinear Thickness Effects written by and published by . This book was released on 1953 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt: A solution to second order in thickness is derived for harmonically oscillating two-dimensional airfoils in supersonic flow. For slow oscillations of an arbitrary profile, the result is found as a series including the third power of frequency. For arbitrary frequencies, the method of solution for any specific profile is indicated, and the explicit solution derived for a single wedge. Nonlinear thickness effects are found generally to reduce the torsional damping, and so enlarge the range of Mach numbers within which torsional instability is possible. This destabilizing effect varies only slightly with frequency in the range involved in dynamic stability analysis, but may reverse to a stabilizing effect at high flutter frequencies. Comparison with a previous solution exact in thickness suggests that nonlinear effects of higher than second order are practically negligible. The analysis utilizes a smoothing technique which replaces the actual problem by one involving no kinked streamlines. This strategem eliminates all consideration of shock waves from the analysis, yet yields the correct solution for problems which actually contain shock waves.
Book Synopsis A Study of Supersonic Flow Past Vibrating Shells and Cascades by : Christian W Brix (Jr)
Download or read book A Study of Supersonic Flow Past Vibrating Shells and Cascades written by Christian W Brix (Jr) and published by . This book was released on 1973 with total page 133 pages. Available in PDF, EPUB and Kindle. Book excerpt: Supersonic flow past oscillating cylindrical shells and oscillating flat-plate cascades is analyzed using linearized characteristics methods. Pressure distributions and generalized aerodynamic forces are computed for arbitrary radius to length ratios, axial and circumferential wave numbers, Mach numbers, and reduced frequencies. Pressure distributions are computed for flat-plate cascades with supersonic leading edge locus for arbitrary solidity, stagger angle, frequency, and interblade phase angle. For comparison, a two-blade solution is developed using the method of singularities. (Modified author abstract).
Book Synopsis Theoretical Analysis of Unsteady Supersonic Flow Around Harmonically Oscillating Turbofan Cascades by : John Everett Caruthers
Download or read book Theoretical Analysis of Unsteady Supersonic Flow Around Harmonically Oscillating Turbofan Cascades written by John Everett Caruthers and published by . This book was released on 1976 with total page 272 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 :9781722404291 Total Pages :58 pages Book Rating :4.4/5 (42 download)
Book Synopsis Flutter Analysis of Supersonic Axial Flow Cascades Using a High Resolution Euler Solver. Part 1 by : National Aeronautics and Space Administration (NASA)
Download or read book Flutter Analysis of Supersonic Axial Flow Cascades Using a High Resolution Euler Solver. Part 1 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents, in two parts, a dynamic aeroelastic stability (flutter) analysis of a cascade of blades in supersonic axial flow. Each blade of the cascade is modeled as a typical section having pitching and plunging degrees of freedom. Aerodynamic forces are obtained from a time accurate, unsteady, two-dimensional cascade solver based on the Euler equations. The solver uses a time marching flux-difference splitting (FDS) scheme. Flutter stability is analyzed in the frequency domain. The unsteady force coefficients required in the analysis are obtained by harmonically oscillating (HO) the blades for a given flow condition, oscillation frequency, and interblade phase angle. The calculated time history of the forces is then Fourier decomposed to give the required unsteady force coefficients. An influence coefficient (IC) method and a pulse response (PR) method are also implemented to reduce the computational time for the calculation of the unsteady force coefficients for any phase angle and oscillation frequency. Part 1, this report, presents these analysis methods and their validation by comparison with results obtained from linear theory for a selected flat plate cascade geometry. A typical calculation for a rotor airfoil is also included to show the applicability of the present solver for airfoil configurations. The predicted unsteady aerodynamic forces for a selected flat plate cascade geometry and flow conditions correlated well with those obtained from linear theory for different interblade phase angles and oscillation frequencies. All the three methods of predicting unsteady force coefficients, namely, HO, IC, and PR, showed good correlations with each other. It was established that only a single calculation with four blade passages is required to calculate the aerodynamic forces for any phase angle for a cascade consisting of any number of blades, for any value of the oscillation frequency. Flutter results, including mistuning effects, for a cascade of s...
Book Synopsis A Study of Supersonic Cascade Flutter by : Henry George Chalkley
Download or read book A Study of Supersonic Cascade Flutter written by Henry George Chalkley and published by . This book was released on 1972 with total page 157 pages. Available in PDF, EPUB and Kindle. Book excerpt: Supersonic flow past oscillating flat plate cascades with supersonic leading-edge locus is analysed using a linearized method of characteristics valid for arbitrary frequencies and an elementary analytical theory valid only for low frequencies of oscillation. These two methods are extensions of previous work by Teipel and Sauer for the single airfoil in an unbounded supersonic flow to the case of airfoils oscillating in cascade. Included is the determination of pressure distributions and both a two-degree-of-freedom (bending and torsion) flutter analysis and a single-degree-of-freedom (torsion) flutter analysis. Numerically determined flutter boundaries are presented for various primary parameters such as, Mach number, solidity, stagger angle, density ratio, structural damping coefficient, and elastic axis position. (Author).
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1969 with total page 1090 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 1978 with total page 1204 pages. Available in PDF, EPUB and Kindle. Book excerpt: Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.
Book Synopsis Symposium Transsonicum III by : Jürgen Zierep
Download or read book Symposium Transsonicum III written by Jürgen Zierep and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 503 pages. Available in PDF, EPUB and Kindle. Book excerpt: Continuing the tradition of the IUTAM Symposia TRANSSONICA, this review of the numerical simulation and physical modelling of transonic flows presents new developments in the fields of computational and experimental aerodynamics. A major topic of the symposium proceedings is the evaluation of present numerical analysis techniques with respect to transonic aerodynamics. In the field of experimental aerodynamics, the high Reynolds number effect and the interference-free testing in transonic wind tunnels are of special interest.
Download or read book The Shock and Vibration Digest written by and published by . This book was released on 1989 with total page 476 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Annual Report of the National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Annual Report of the National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1955 with total page 822 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes the Committee's Reports no. 1-1058, reprinted in v. 1-37.
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).
