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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 : John G. Presnell (Jr.)
Publisher :
ISBN 13 :
Total Pages : 24 pages
Book Rating : 4.:/5 (31 download)
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.
Author : W. J. Tuovila
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.:/5 (31 download)
Download or read book Supersonic Panel Flutter Test Results for Flat-fiber-glass Sandwich Panels with Foamed Cores written by W. J. Tuovila and published by . This book was released on 1961 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flutter tests were made on flat panels having a 1/4-inch-thick plastic-foam core covered with thin fiber-glass laminates. The testing was done in the Langley Unitary Plan wind tunnel at Mach numbers from 1.76 to 2.87. The flutter boundary for these panels was found to be near the flutter boundary of thin metal panels when compared on the basis of an equivalent panel stiffness. The results also demonstrated that the depth of the cavity behind the panel has a pronounced influence on flutter. Changing the cavity depth from 1 1/2 inches to 1/2 inch reduced the dynamic pressure at start of flutter by 40 percent. No flutter was obtained when the spacers on the back of the panel were against the bottom of the cavity. (Author).
Author : Herman L. Bohon
Publisher :
ISBN 13 :
Total Pages : 68 pages
Book Rating : 4.:/5 (31 download)
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.
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 : Michael L. Nacht
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (31 download)
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:
Author : Tilak R. Lall
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.:/5 (317 download)
Download or read book Interstage Adapter Panel Flutter on Atlas- Centaur AC-2, AC-3, and AC-4 Vehicles written by Tilak R. Lall and published by . This book was released on 1965 with total page 20 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 : 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 : Lawrence Duncan Guy
Publisher :
ISBN 13 :
Total Pages : 48 pages
Book Rating : 4.:/5 (31 download)
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:
Author : Herman L. Bohon
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)
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:
Author : L. E. Goodman
Publisher :
ISBN 13 :
Total Pages : 92 pages
Book Rating : 4.3/5 (91 download)
Download or read book Supersonic Speed Flutter Analysis of Circular Panels with Edges Elastically Restrained Against Rotation written by L. E. Goodman and published by . This book was released on 1960 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 : Charles P. Shore
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (31 download)
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:
Author : Herman L. Bohon
Publisher :
ISBN 13 :
Total Pages : 48 pages
Book Rating : 4.:/5 (31 download)
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:
Author : Robert W. Hess
Publisher :
ISBN 13 :
Total Pages : 98 pages
Book Rating : 4.:/5 (31 download)
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.
Author : Herman L. Bohon
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)
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.
