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Author : William Judson Anderson
Publisher :
ISBN 13 :
Total Pages : 262 pages
Book Rating : 4.:/5 (437 download)
Download or read book Studies in Panel Flutter at Higher Mach Numbers written by William Judson Anderson and published by . This book was released on 1963 with total page 262 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : E. H. Dowell
Publisher :
ISBN 13 :
Total Pages : 396 pages
Book Rating : 4.3/5 (91 download)
Download or read book Experimental and Theoretical Panel Flutter Studies in the Mach Number Range of 1.0 to 5.0 written by E. H. Dowell and published by . This book was released on 1963 with total page 396 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Maurice A. Sylvester
Publisher :
ISBN 13 :
Total Pages : 16 pages
Book Rating : 4.3/5 (91 download)
Download or read book Experimental and Theoretical Studies of Panel Flutter at Mach Number 1.2 to 3.0 written by Maurice A. Sylvester and published by . This book was released on 1955 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John Dugundji
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (813 download)
Download or read book Theoretical Considerations of Panel Flutter at High Supersonic Mach Numbers written by John Dugundji and published by . This book was released on 1965 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : M. H. Lock
Publisher :
ISBN 13 :
Total Pages : 180 pages
Book Rating : 4.3/5 (91 download)
Download or read book Comparative Experimental and Theoretical Studies of the Flutter of Flat Panels in a Low Supersonic Flow written by M. H. Lock and published by . This book was released on 1961 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of panel flutter experiments were performed in the GALCIT transonic wind tunnel. The preflutter panel motion and the motion during flutter were studied in detail. Flutter boundaries were obtained between Mach numbers 1.15 and 1.5. Three analytical studies of the flutter phenomenon, based upon conventional assumptions, are presented which facilitate comparison between theory and experiment. A detailed comparison between the theoretical and experimental results reveals considerable disagreement in the flutter boundaries at supersonic Mach numbers less than 1.4. The agreement between theory and experiment improves at the higher Mach numbers. The theory appears inadequate for the prediction of flutter boundaries at the lower supersonic Mach numbers. A possible cause of this inadequacy of the theory is discussed. (Author).
Author : Maurice A. Sylvester
Publisher :
ISBN 13 :
Total Pages : 42 pages
Book Rating : 4.:/5 (31 download)
Download or read book Experimental Studies of Flutter of Buckled Rectangular Panels at Mach Numbers from 1.2 to 3.0 Including Effects of Pressure Differential and of Panel Width-length Ratio written by Maurice A. Sylvester and published by . This book was released on 1961 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Maurice A. Sylvester
Publisher :
ISBN 13 :
Total Pages : 32 pages
Book Rating : 4.3/5 (91 download)
Download or read book Some Experimental Studies of Panel Flutter at Mach Number 1.3 written by Maurice A. Sylvester and published by . This book was released on 1952 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : M. H. Lock
Publisher :
ISBN 13 :
Total Pages : 160 pages
Book Rating : 4.:/5 (33 download)
Download or read book Comparative Experimental and Theoretical Studies of the Flutter of Flate Panels in a Low Supersonic Flow written by M. H. Lock and published by . This book was released on 1961 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of panel flutter experiments were performed in the GALCIT transonic wind tunnel. The preflutter panel motion and the motion during flutter were studied in detail. Flutter boundaries were obtained between Mach numbers 1.15 and 1.5. Three analytical studies of the flutter phenomenon, based upon conventional assumptions, are presented which facilitate comparison between theory and experiment. A detailed comparison between the theoretical and experimental results reveals considerable disagreement in the flutter boundaries at supersonic Mach numbers less than 1.4. The agreement between theory and experiment improves at the higher Mach numbers. The theory appears inadequate for the prediction of flutter boundaries at the lower supersonic Mach numbers. A possible cause of this inadequacy of the theory is discussed.
Author : M. H. Lock
Publisher :
ISBN 13 :
Total Pages : 158 pages
Book Rating : 4.3/5 (91 download)
Download or read book The Flutter of Two-bay Flat Panels of Infinite Span at Supersonic Mach Numbers written by M. H. Lock and published by . This book was released on 1964 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt: The flutter of two-bay clamped-edge and simply supported panels at supersonic Mach numbers is studied to determine the influence of structural and aerodynamic coupling. It is found that the effect of structural coupling between the panel bays is unimportant both for the 'single-degree-offreedom' flutter modes that are critical at the lower supersonic Mach numbers and for the critical coupled flutter modes that develop at higher supersonic Mach numbers. The effect of aerodynamic coupling is found to be of importance for the 'single-degree-of-freedom' flutter modes only. Furthermore, the severity of this effect is highly dependent upon the panel boundary conditions. (Author).
Author :
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (227 download)
Download or read book Comparative Experimental and Theoretical Studies of the Flutter of Flat Panels in a Low Supersonic Flow written by and published by . This book was released on 1961 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of panel flutter experiments were performed in the GALCIT transonic wind tunnel. The preflutter panel motion and the motion during flutter were studied in detail. Flutter boundaries were obtained between Mach numbers 1.15 and 1.5. Three analytical studies of the flutter phenomenon, based upon conventional assumptions, are presented which facilitate comparison between theory and experiment. A detailed comparison between the theoretical and experimental results reveals considerable disagreement in the flutter boundaries at supersonic Mach numbers less than 1.4. The agreement between theory and experiment improves at the higher Mach numbers. The theory appears inadequate for the prediction of flutter boundaries at the lower supersonic Mach numbers. A possible cause of this inadequacy of the theory is discussed. (Author).
Author : Harry L. Runyan
Publisher :
ISBN 13 :
Total Pages : 16 pages
Book Rating : 4.3/5 (91 download)
Download or read book Flutter at Very High Speeds written by Harry L. Runyan and published by . This book was released on 1957 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper is concerned with a discussion of some of the problems of flutter and aeroelasticity that are or may be important at high speeds. Various theoretical procedures for treating high Mach number flutter are reviewed. Application of two of these methods, namely, the Van Dyke method and piston-theory method, is made to a specific example and compared with linear two- and three-dimensional results. It is shown that the effects of thickness and airfoil shape are destabilizing as compared with linear theory at high Mach number. In order to demonstrate the validity of these large predicted effects, experimental flutter results are shown for two rectangular wings at Mach numbers of 6.86 and 3. The results of nonlinear piston-theory calculations were in good agreement with experiment, whereas the results of using two- and three-dimensional linear theory were not. In addition, some results demonstrating the importance of including camber modes in a flutter analysis are shown, as well as a discussion of one case of flutter due to aerodynamic heating.
Author : Maurice A. Sylvester
Publisher :
ISBN 13 :
Total Pages : 37 pages
Book Rating : 4.:/5 (11 download)
Download or read book Experimental Studies of Flutter of Buckled Rectangular Panels at Mach Numbers from 1.2 to 3.0 Including Effects of Pressure Differential and of Panel Width-length Ratio written by Maurice A. Sylvester and published by . This book was released on 1955 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Maurice A. Sylvester
Publisher :
ISBN 13 :
Total Pages : 25 pages
Book Rating : 4.:/5 (249 download)
Download or read book Some Experimental Studies of Panel Flutter at Mach Number 1.3 written by Maurice A. Sylvester and published by . This book was released on 1957 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental studies of panel flutter using thin metal plates were conducted at a Mach number of 1.3 to verify its existence and to study the effects of some structural parameters on the flutter characteristics. The effects of tensile forces and buckling were studied on panels clamped front and rear, in addition to initially buckled panels clamped on all four edges. Panel flutter was obtained under controlled laboratory conditions and it was found that tensile forces, shortening the panels, and increasing the bending stiffness were effective means for eliminating flutter. Buckled panels were more susceptible to flutter than unbuckled panels. No apparent systematic trends in the flutter modes or frequencies could be observed.
Author :
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (227 download)
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).
Author : Herbert J. Cunningham
Publisher :
ISBN 13 :
Total Pages : 60 pages
Book Rating : 4.:/5 (31 download)
Download or read book Flutter Analysis of Flat Rectangular Panels Based on Three-dimensional Supersonic Unsteady Potential Flow written by Herbert J. Cunningham and published by . This book was released on 1967 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: A systematic analytical procedure has been developed for computing flutter characteristics of rectangular panels with stream-aligned side edges, based on air forces from three-dimensional linearized supersonic unsteady potential flow. The procedure has particular usefulness in the low supersonic speed range where static and quasi-static aerodynamic approximations are considered to be least valid and can provide bases of comparison for some of the simpler types of analysis. The panel is considered to be finely divided into many boxes, and the aerodynamic influence coefficients between all pairs of boxes are obtained by numerical integration. The flutter analysis is a modal type, which readily coordinates with the aerodynamic box method, and can be used for calculating the flutter stability of any flat or nearly flat panel, whether of isotropic or anisotropic stiffness, and of buckled panels for which the flutter is a small-amplitude, simple harmonic, superimposed motion to which linear theory is applicable. A number of results are presented for flat unstressed, isotropic panels with simply supported edges and with clamped edges. For clamped-edge aluminum panels with length-width ratio of 2 at sea level, the panel flutter parameters are tabulated for eight Mach numbers ranging from 1.02 to 2.0. For Mach 1.3, fluter boundaries are plotted for length-width ratios from 0 to 10 for simply supported edges and from 0 to 4 for clamped edges so that design values can be read for a wide range of panel materials and air densities. Appendix A delineates the way in which the natural mode characteristics were developed for calculating the presented flutter results without the need for double-precision arithmetic. Appendix B provides formulas for conversion among a number of types of flutter solution parameters in current use. Appendix C describes a way to economize computer time for the large matrix multiplication required.
Author : C. H. Hodson
Publisher :
ISBN 13 :
Total Pages : 550 pages
Book Rating : 4.3/5 (91 download)
Download or read book Commercial Supersonic Tansport Panel Flutter Studies written by C. H. Hodson and published by . This book was released on 1964 with total page 550 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of analog computer and wind tunnel studies are discussed. The application of the results to design of skin panels for the commercial supersonic transport is discussed. Optimum skin panel design, within the framework of presently existing panel flutter knowledge, is finally discussed. (Author).
Author : D. R. Kobett
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (31 download)
Download or read book Flutter of Multiple-streamwise Bay Rectangular Panels at Low Supersonic Mach Number written by D. R. Kobett and published by . This book was released on 1966 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
