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Comparative Experimental And Theoretical Studies Of The Flutter Of Flate Panels In A Low Supersonic Flow
Download Comparative Experimental And Theoretical Studies Of The Flutter Of Flate Panels In A Low Supersonic Flow full books in PDF, epub, and Kindle. Read online Comparative Experimental And Theoretical Studies Of The Flutter Of Flate Panels In A Low Supersonic Flow ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Comparative Experimental and Theoretical Studies of the Flutter of Flate Panels in a Low Supersonic Flow by : M. H. Lock
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.
Book Synopsis Comparative Experimental and Theoretical Studies of the Flutter of Flat Panels in a Low Supersonic Flow by : M. H. Lock
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).
Book Synopsis Comparative Experimental and Theoretical Studies of the Flutter of Flat Panels in a Low Supersonic Flow by :
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).
Book Synopsis Experimental and Theoretical Panel Flutter Studies in the Mach Number Range of 1.0 to 5.0 by : E. H. Dowell
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:
Book Synopsis Experimental and Theoretical Studies of Panel Flutter at Mach Number 1.2 to 3.0 by : Maurice A. Sylvester
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:
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 376 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
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:
Book Synopsis Experimental Investigation of Flutter at Mach 3 of Rotationally Restrained Panels and Comparison with Theory by : Charles P. Shore
Download or read book Experimental Investigation of Flutter at Mach 3 of Rotationally Restrained Panels and Comparison with Theory written by Charles P. Shore and published by . This book was released on 1969 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Theoretical Flutter Analysis of Flat Rectangular Panels in Uniform Coplanar Flow with Arbitrary Direction by : Eldon Eugene Kordes
Download or read book Theoretical Flutter Analysis of Flat Rectangular Panels in Uniform Coplanar Flow with Arbitrary Direction written by Eldon Eugene Kordes and published by . This book was released on 1962 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flutter Analysis of Flat Rectangular Panels Based on Three-dimensional Supersonic Unsteady Potential Flow by : Herbert J. Cunningham
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.
Book Synopsis Experimental Investigation of Orthotropic Panel Flutter at Arbitrary Yaw Angles, and Comparison with Theory by : Peter Shyprykevich
Download or read book Experimental Investigation of Orthotropic Panel Flutter at Arbitrary Yaw Angles, and Comparison with Theory written by Peter Shyprykevich and published by . This book was released on 1973 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flutter characteristics for yaw angles between 15 deg and 90 deg were determined experimentally for two types of corrugation-stiffened panels: those with weak twisting stiffness and those with strong twisting stiffness. By mounting the panels on a remotely controlled turntable, good definition of the flutter boundaries was obtained by rotating the panels into and out of flutter. Flutter tests were conducted at M = 2 and M = 1.6. Before testing, vibration tests and analyses were also performed. The experimental flutter data is compared with flutter theory for orthotropic panels utilizing quasi-steady aerodynamics. Five different corrugated panels were tested consisting of one single skin panel having a length-to-width ratio of 5 on clamped supports and four different square double skin panels on discrete flexible supports. The investigation indicated that flutter speed for corrugated panels is highly dependent on yaw angle. Reasonable flutter correlation between analysis and test was obtained for moderate yaw angles, but extreme sensitivity to structural parameters made the correlation at large yaw angles uncertain.
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 Some Experimental Studies of Panel Flutter at Mach Number 1.3 by : Maurice A. Sylvester
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:
Book Synopsis Accurate Linearized Theory of Supersonic Flutter Panels; Set Up of Problem and General Solution by : Dun Min-De
Download or read book Accurate Linearized Theory of Supersonic Flutter Panels; Set Up of Problem and General Solution written by Dun Min-De and published by . This book was released on 1966 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report represents an effort of systematically investigating the flutter movement of panels on the basis of linearized theory at supersonic flow around. The report consists of five parts: (1) arrangement of problem and general solution; (2) theorem of subsistence; (3) autooscillations in near and hypersonic flow; (4) stability of multispan; (5) autooscillations of trapezoidal plate with consideration of finite effect. (Author).
Book Synopsis Experimental and Analytical Investigation of the Flutter of Flat Built-up Panels Under Streamwise Inplane Load by : Robert W. Hess
Download or read book Experimental and Analytical Investigation of the Flutter of Flat Built-up Panels Under Streamwise Inplane Load written by Robert W. Hess and published by . This book was released on 1970 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: The flutter of 13 panels subject to streamwise inplane load at Mach numbers of 1.57 and 1.96 has been investigated. Panel length-width ratios ranged from 1 to 4.2. The experimental flutter boundary was compared with an analytical flutter boundary for six of the panels. Damping, both aerodynamic and structural, was found to have a pronounced effect on the analytical flutter boundary. The agreement between analysis and experiment was dependent upon how structural damping was introduced in the formulation of the problem.
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1967 with total page 848 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flutter at Mach 3 of Thermally Stressed Panels and Comparison with Theory for Panels with Edge Rotational Restraint by : John L. Shideler
Download or read book Flutter at Mach 3 of Thermally Stressed Panels and Comparison with Theory for Panels with Edge Rotational Restraint written by John L. Shideler and published by . This book was released on 1966 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
