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Research On Panel Flutter Of Cylindrical Shells
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Book Synopsis Research on Panel Flutter of Cylindrical Shells by :
Download or read book Research on Panel Flutter of Cylindrical Shells written by and published by . This book was released on 1964 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical study was made on the panel flutter characteristics of a ring and longeron stiffened circular cylindrical shell at high supersonic Mach numbers. This study is an extension of an earlier program and uses the cyclic reduction procedure developed there to simplify the flutter analysis. This actual reduction procedure has been included in this report for completeness. An improved modal analysis was employed in this study which leads to an increased understanding of the flutter behavior of such complex structures at the high supersonic Mach numbers. A method for extending the above analysis to the lower supersonic Mach numbers is also discussed. An investigation of the aerodynamic pressures on cylindrical shells in unsteady supersonic potential flow has also been carried out. A general solution for these aerodynamic pressures was obtained which is valid at both the high and low supersonic Mach numbers. The general solution was expressed in terms of Randall functions by reducing the unsteady flow problem to an equivalent steady flow problem through an appropriate transformation. Certain limiting cases of this general solution are presented along with their well-known flat plate counterparts. Finally, an analytical approximation is developed for the Randall functions which would be useful in a cylindrical shell panel flutter analysis. (Author).
Book Synopsis PANEL FLUTTER OF CYLINDRICAL SHELLS by : W.J. Anderson
Download or read book PANEL FLUTTER OF CYLINDRICAL SHELLS written by W.J. Anderson and published by . This book was released on 1967 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research on Panel Flutter of Cylindrical Shells by : Ronald O. Stearman
Download or read book Research on Panel Flutter of Cylindrical Shells written by Ronald O. Stearman and published by . This book was released on 1964 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical study was made on the panel flutter characteristics of a ring and longeron stiffened circular cylindrical shell at high supersonic Mach numbers. This study is an extension of an earlier program and uses the cyclic reduction procedure developed there to simplify the flutter analysis. This actual reduction procedure has been included in this report for completeness. An improved modal analysis was employed in this study which leads to an increased understanding of the flutter behavior of such complex structures at the high supersonic Mach numbers. A method for extending the above analysis to the lower supersonic Mach numbers is also discussed. An investigation of the aerodynamic pressures on cylindrical shells in unsteady supersonic potential flow has also been carried out. A general solution for these aerodynamic pressures was obtained which is valid at both the high and low supersonic Mach numbers. The general solution was expressed in terms of Randall functions by reducing the unsteady flow problem to an equivalent steady flow problem through an appropriate transformation. Certain limiting cases of this general solution are presented along with their well-known flat plate counterparts. Finally, an analytical approximation is developed for the Randall functions which would be useful in a cylindrical shell panel flutter analysis. (Author).
Book Synopsis Recent Contributions to Experiments on Cylindrical Shell Panel Flutter by : W. Horn
Download or read book Recent Contributions to Experiments on Cylindrical Shell Panel Flutter written by W. Horn and published by . This book was released on 1971 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental studies have been carried out on the aeroelastic stability of several cylindrical shell configurations under various internal stress and supersonic flow conditions. These experiments were conducted in the AEDC Propulsion Wind Tunnel Facility over the Mach number range 1.2 to 3.5. Some of the initial experiments demonstrated that the still-air buckling characteristics of thin cylindrical shells were not significantly influenced by the supersonic air stream. The wealth of still air buckling data can consequently be employed to determine the buckling loads of cylindrical shells exposed to a supersonic flow field. (Author).
Book Synopsis A Theoretical Study of Cylindrical Shell Panel Flutter by : Lawrence Lee Carter
Download or read book A Theoretical Study of Cylindrical Shell Panel Flutter written by Lawrence Lee Carter and published by . This book was released on 1966 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aeroelasticity of Plates and Shells by : E.H. Dowell
Download or read book Aeroelasticity of Plates and Shells written by E.H. Dowell and published by Springer Science & Business Media. This book was released on 1974-11-30 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Panel Flutter of a Cylindrical Shell of Finite Length by : Sainsbury Lee Strack
Download or read book Supersonic Panel Flutter of a Cylindrical Shell of Finite Length written by Sainsbury Lee Strack and published by . This book was released on 1959 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Nonlinear Flutter of a Circular Cylindrical Shell in Supersonic Flow by : David A. Evensen
Download or read book Nonlinear Flutter of a Circular Cylindrical Shell in Supersonic Flow written by David A. Evensen and published by National Research Council of Canada. This book was released on 1967 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aeroelastic Vibrations and Stability of Plates and Shells by : Sergey D. Algazin
Download or read book Aeroelastic Vibrations and Stability of Plates and Shells written by Sergey D. Algazin and published by Walter de Gruyter GmbH & Co KG. This book was released on 2014-12-11 with total page 234 pages. Available in PDF, EPUB and Kindle. Book excerpt: Back-action of aerodynamics onto structures such as wings cause vibrations and may resonantly couple to them, thus causing instabilities (flutter) and endangering the whole structure. By careful choices of geometry, materials and damping mechanisms, hazardous effects on wind engines, planes, turbines and cars can be avoided. Besides an introduction into the problem of flutter, new formulations of flutter problems are given as well as a treatise of supersonic flutter and of a whole range of mechanical effects. Numerical and analytical methods to study them are developed and applied to the analysis of new classes of flutter problems for plates and shallow shells of arbitrary plane form. Specific problems discussed in the book in the context of numerical simulations are supplemented by Fortran code examples (available on the website).
Book Synopsis Aerodynamic Forces on a Cylindrical Shell in Panel Flutter by : Maurice Holt
Download or read book Aerodynamic Forces on a Cylindrical Shell in Panel Flutter written by Maurice Holt and published by . This book was released on 1958 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Research Review written by and published by . This book was released on 1969 with total page 324 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Recent Experimental Studies on the Aeroelastic Stability of Thin Cylindrical Shells. Part I. an Experimental Study of the Supersonic Flow Field Over an Aeroelastic Ogive Cylinder Model with Boundary Layer Control by : Philip L. Daily
Download or read book Some Recent Experimental Studies on the Aeroelastic Stability of Thin Cylindrical Shells. Part I. an Experimental Study of the Supersonic Flow Field Over an Aeroelastic Ogive Cylinder Model with Boundary Layer Control written by Philip L. Daily and published by . This book was released on 1970 with total page 153 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study was conducted as the first phase in a program to determine the influence of a compressible viscous boundary layer on cylindrical shell panel flutter. In the first part of the experiment, a study was conducted to provide data on the uniformity of the surface pressure distribution over the region of the flutter model where the thin cylindrical shells were mounted for the flutter experiments. The measured data confirmed that for all flow conditions above Mach Number 1.2, no significant pressure gradient existed over the region of the model where the flutter shells were mounted for testing. A study was then conducted to determine the effectiveness of the boundary layer control system for increasing the boundary layer thickness over the region of the model where the flutter shells were mounted. The boundary layer control system proved to be quite effective and under optimum conditions could increase the displacement and momentum thicknesses by a factor of 10. In general, the displacement and momentum thicknesses could be increased by at least 50% for most of the operating conditions of the wind tunnels by maximum activation of the boundary layer control systems. Finally boundary layer transition and profile similarity studies were conducted to determine the range of free stream flow conditions and boundary layer control activation rates where boundary layer profile similarity could be achieved over the test shell area of the model. The results indicate that similar laminar or turbulent boundary layer profiles can be maintained over the test region of the model for flow conditions where panel flutter can be expected to occur. (Author).
Book Synopsis Some Aspects of Cylindrical Shell Panel Flutter by : L. L. Carter
Download or read book Some Aspects of Cylindrical Shell Panel Flutter written by L. L. Carter and published by . This book was released on 1967 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: The investigation makes a direct comparison of cylindrical shell panel flutter boundaries obtained analytically with recent experimental boundaries reported in the literature. Further, an attempt was made to explain the discrepancies of the comparison through refinements of some structural aspects of the analysis. The non-linear Donnell shell theory is utilized together with the first-order, high Mach number approximation to the linear potential flow theory. The axisymmetric pre-flutter deformation, due to internal pressurization and axial loading of the shell in the presence of an air stream, is included in the analysis as the configuration about which the shell flutters. The structural boundary conditions assumed for the flutter state are the simply-supported, zero-traction boundary conditions as well as the classical, simply-supported boundary conditions. The problem associated with the pre-deformation state of the shell was solved exactly, whereas the approximate technique due to B.G. Galerkin was employed to solve the linearized system of flutter equations. In general, it is shown that agreement exists between the theory and experiment only in the region of small amounts of static loading of the shell.
Book Synopsis The Effect of Second Order Elastic Terms in Supersonic Panel Flutter of Finite Cylindrical Shells by : James C. S. Meng
Download or read book The Effect of Second Order Elastic Terms in Supersonic Panel Flutter of Finite Cylindrical Shells written by James C. S. Meng and published by . This book was released on 1970 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis for the flutter boundary of a finite isotropic cylindrical shell under no static stress in a supersonic free stream is carried out at Mach numbers from 3-10. The effect of second order terms in the elastic equilibrium equation, which was not considered by Li (1967), is examined in detail. The aerodynamic load is computed following the same approximation usedby Li (1967), and the elastic displacement of the shell is resolved into a linear combination of sine functions to satisfy the clamped boundary condition at one end and simply supported conditions at the other end. This homogeneous system is solved by Galerkin's method. Then the resultant matrix is transformed into a convenient form, having the same characteristic equation, and expressed in triangular form by means of QR-transformations. The required eigenvalues are the diagonal elements of the transformed matrix. The flutter boundary is defined as the curve where the imaginary part of the eigenvalue becomes negative. It is found that the effect of the second order terms is small. (Author).
Book Synopsis Research Review by : United States. Air Force. Office of Aerospace Research
Download or read book Research Review written by United States. Air Force. Office of Aerospace Research and published by . This book was released on 1969 with total page 346 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis OAR Research Review by : United States. Air Force. Office of Aerospace Research
Download or read book OAR Research Review written by United States. Air Force. Office of Aerospace Research and published by . This book was released on 1968 with total page 528 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis U.S. Government Research Reports by :
Download or read book U.S. Government Research Reports written by and published by . This book was released on 1964 with total page 2180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
