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Panel Flutter
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Book Synopsis Experimental Panel Flutter Results for Some Flat and Curved Titanium Skin Panels at Supersonic Speeds by : John G. Presnell (Jr.)
Download or read book Experimental Panel Flutter Results for Some Flat and Curved Titanium Skin Panels at Supersonic Speeds written by John G. Presnell (Jr.) and published by . This book was released on 1963 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of tests at Mach numbers from 1.72 to 2.62 on panels having a thickness from O. Ol5 to 0.045 inch, length-width ratio from 0.36 to 2.76, and radius-thickness ratio from 600 to infinity are presented. These results indicate a strong influence of differential pressure, which caused buckling on the flutter mode and on the dynamic pressure flutter for the curved panels. Results for both the flat and curved pan 5 fall within an extrapolation of an existing experimental panel flutter boundary.
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 Panel Flutter Tests on Full-scale X-15 Lower Vertical Stabilizer at Mach Number of 3.0 by : Herman L. Bohon
Download or read book Panel Flutter Tests on Full-scale X-15 Lower Vertical Stabilizer at Mach Number of 3.0 written by Herman L. Bohon and published by . This book was released on 1962 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: "Panel flutter tests were conducted on two-full scale vertical stabilizers of the X-15 airplane at a Mach number of 3.0 in the Langley 9- by 6-foot thermal structures tunnel at dynamic pressures from 1,500 psf to 5,000 psf and stagnation temperatures from 300° F to 600° F. Flutter boundaries were obtained for four of the five distinct types of panels which make up the vertical sides of the stabilizers. The boundaries consisted of a flat-panel boundary and a thermally buckled-panel boundary. The flat-panel boundaries were characterized by a reduction in dynamic pressure with increasing skin temperature; whereas, after thermal buckling the trend was reversed. The minimum dynamic pressure for flutter occurred at the intersection of the flat-panel and buckled-panel boundaries and represented a large reduction in the dynamic pressure over the extrapolated, unstressed value. As a result of panel flutter, three of the five distinct types of panels were modified to provide the required flutter margin on the design flight dynamic pressure of the aircraft."--Summary.
Book Synopsis Panel Flutter Studies of Boost-vehicle Full-scale Flight Insulation Panels by : Michael L. Nacht
Download or read book Panel Flutter Studies of Boost-vehicle Full-scale Flight Insulation Panels written by Michael L. Nacht and published by . This book was released on 1967 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Flutter of Aerodynamically Heated Aluminum-alloy and Stainless-steel Panels with Length-width Ratio of 10 at Mach Number of 3.0 by : Lawrence Duncan Guy
Download or read book Flutter of Aerodynamically Heated Aluminum-alloy and Stainless-steel Panels with Length-width Ratio of 10 at Mach Number of 3.0 written by Lawrence Duncan Guy and published by . This book was released on 1962 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : Maurice A. Sylvester
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:
Book Synopsis Flutter of Corrugation-stiffened Panels at Mach 3 and Comparison with Theory by : Herman L. Bohon
Download or read book Flutter of Corrugation-stiffened Panels at Mach 3 and Comparison with Theory written by Herman L. Bohon and published by . This book was released on 1968 with total page 36 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 Flutter of Flat Rectangular Orthotropic Panels with Biaxial Loading and Arbitrary Flow Direction by : Herman L. Bohon
Download or read book Flutter of Flat Rectangular Orthotropic Panels with Biaxial Loading and Arbitrary Flow Direction written by Herman L. Bohon and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 98 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.
Book Synopsis Flutter Design of Stiffened-skin Panels for Hypersonic Aircraft by : Herman L. Bohon
Download or read book Flutter Design of Stiffened-skin Panels for Hypersonic Aircraft written by Herman L. Bohon and published by . This book was released on 1969 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Design factors for flutter control of stiffened exterior skin panels for hypersonic aircraft.
Book Synopsis Application of Transtability Concept to Flutter of Finite Panels and Experimental Results by : Sidney C. Dixon
Download or read book Application of Transtability Concept to Flutter of Finite Panels and Experimental Results written by Sidney C. Dixon and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Natural Vibration and Flutter of Elastically Supported Corrugation-stiffened Panels by : Walter L. Heard
Download or read book Natural Vibration and Flutter of Elastically Supported Corrugation-stiffened Panels written by Walter L. Heard and published by . This book was released on 1970 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: The natural vibration and flutter characteristics of two corrugation-stiffened panels were studied experimentally and theoretically to determine the effects of finite deflectional, rotational, and torsional stiffnesses of the boundary supports. Flutter tests were conducted at a Mach number of 3. The experimental data are compared with results from a flutter theory for orthotropic panels which includes the effects of finite support stiffnesses as well as uniform in-plane loading of the panel. The investigation indicates that finite deflectional, rotational, and torsional stiffnesses of the boundary supports must be accounted for in the theory in order to match experimental natural frequencies of the test panels. However, it is concluded that structural damping (neglected in the theory) strongly influenced the flutter behavior of the test panels. Furthermore, the theory shows that the addition of torsional stiffening at the supports is a definite asset for increasing flutter dynamic pressure and may be extremely important in the design of panels for application at hypersonic speeds where thermal expansion may be desired.
Book Synopsis Effects of Structural Damping on Flutter of Stressed Panels by : Charles P. Shore
Download or read book Effects of Structural Damping on Flutter of Stressed Panels written by Charles P. Shore and published by . This book was released on 1969 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flutter of Buckled, Simply Supported, Rectangular Panels at Supersonic Speeds by : Robert William Fralich
Download or read book Flutter of Buckled, Simply Supported, Rectangular Panels at Supersonic Speeds written by Robert William Fralich and published by . This book was released on 1968 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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).
