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Experimental Investigation At Mach Number 3 0 Of Effects Of Thermal Stress And Buckling On Flutter Characteristics Of Flat Single Bay Panels Of Length Width Ration 0 96 Book in PDF, ePub and Kindle version is available to download in english. Read online anytime anywhere directly from your device. Click on the download button below to get a free pdf file of Experimental Investigation At Mach Number 3 0 Of Effects Of Thermal Stress And Buckling On Flutter Characteristics Of Flat Single Bay Panels Of Length Width Ration 0 96 book. This book definitely worth reading, it is an incredibly well-written.
Author : Sidney C. Dixon
Publisher : Unknown
Page : 32 pages
File Size : 46,6 Mb
Release : 1961
Category : Buckling (Mechanics)
ISBN : UIUC:30112106872317
Author : Sidney C. Dixon
Publisher : Unknown
Page : 32 pages
File Size : 51,7 Mb
Release : 1963
Category : Airframes
ISBN : UIUC:30112106864496
Author : Robert W. Hess,Frederick W. Gibson (NASA researcher.)
Publisher : Unknown
Page : 32 pages
File Size : 41,5 Mb
Release : 1962
Category : Mach number
ISBN : UIUC:30112106873463
"An investigation was made of the effects of compressive stress on the flutter of a curved and a flat panel. The curved panel which was 0.0075-inch-thick stainless steel with a length-width ratio of 2.13 and a radius-to-thickness ratio of 1.133 was tested at a Mach number of 1.97. A flat aluminum panel, 0.032 inch thick with a length-width ratio of 2.13, was tested at Mach numbers of 1.63 to 1.84. The dynamic pressure at flutter decreased with increased axial compressive stress to a point where the panel was loaded to a stress near the calculated critical buckling stress. Beyond this point, the dynamic pressure at flutter increased with increasing compressive stress. The results of the flat-panel flutter tests indicate that caution should be exercised in using empirical panel fluter boundaries."--Summary.
Author : Robert W. Hess
Publisher : Unknown
Page : 102 pages
File Size : 45,9 Mb
Release : 1970
Category : Damping (Mechanics)
ISBN : NASA:31769000423510
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 : Maurice A. Sylvester,Herbert C. Nelson,Herbert J. Cunningham
Publisher : Unknown
Page : 16 pages
File Size : 43,6 Mb
Release : 1955
Category : Aeroelasticity
ISBN : UOM:39015086465864
Author : John L. Shideler
Publisher : Unknown
Page : 34 pages
File Size : 51,9 Mb
Release : 1966
Category : Buckling (Mechanics)
ISBN : UIUC:30112106774646
Author : E. H. Dowell,H. M. Voss
Publisher : Unknown
Page : 396 pages
File Size : 41,7 Mb
Release : 1963
Category : Flutter (Aerodynamics)
ISBN : UOM:39015095304138
Author : Maurice A. Sylvester,John E. Baker
Publisher : Unknown
Page : 32 pages
File Size : 48,9 Mb
Release : 1952
Category : Aeroelasticity
ISBN : UOM:39015086465088
Author : Harry L. Runyan
Publisher : Unknown
Page : 16 pages
File Size : 48,5 Mb
Release : 1957
Category : Aerodynamic heating
ISBN : UOM:39015086466094
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,John E. Baker
Publisher : Unknown
Page : 25 pages
File Size : 45,5 Mb
Release : 1957
Category : Plates (Engineering)
ISBN : OCLC:249896773
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 : Lawrence Duncan Guy
Publisher : Unknown
Page : 48 pages
File Size : 45,9 Mb
Release : 1962
Category : Flutter (Aerodynamics)
ISBN : UIUC:30112106636928
Author : John G. Presnell (Jr.)
Publisher : Unknown
Page : 24 pages
File Size : 52,7 Mb
Release : 1963
Category : Aerodynamics, Supersonic
ISBN : UIUC:30112106689661
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 : Herman L. Bohon
Publisher : Unknown
Page : 36 pages
File Size : 47,8 Mb
Release : 1968
Category : Flutter (Aerodynamics)
ISBN : UIUC:30112106687707
Author : E.H. Dowell
Publisher : Springer Science & Business Media
Page : 166 pages
File Size : 41,7 Mb
Release : 1974-11-30
Category : Science
ISBN : 9028604049
Author : Thomas Henry Gordon Megson
Publisher : Hodder Education
Page : 0 pages
File Size : 41,5 Mb
Release : 1990
Category : Aeroelasticity
ISBN : 0713136812
This book provides a self-contained course in aircraft structures which contains not only the fundamentals of elasticity and aircraft structural analysis but also the associated topics of airworthiness and aeroelasticity.
