Download or read book An Analytical and Experimental Investigation of the Aeroelastic Stability of Cylindrical Shells at the Subsonic and Supersonic Mach Numbers written by Walter Julian Horn and published by . This book was released on 1972 with total page 318 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Analytical and Experimental Investigation of the Aeroelastic S973ility of Cylindrical Shells at the Subsonic and Supersonic Mach Numbers written by Walter J. Horn and published by . This book was released on 1972 with total page 318 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Analytical and Experimental Investigation of the Aeroelastic Stability of Cyllindrical Shells at the Subsonic and Supersonic Mach Numbers written by Walter Julian Horn and published by . This book was released on 1972 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 316 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 912 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Theoretical Investigation on the Aeroelastic Stability of Isotropic Cylindrical Shells at Both the High and Low Supersonic Mach Numbers written by Larry Carter and published by . This book was released on 1966 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: The study includes an investigation on the aeroelastic stability of thin isotropic cylindrical shells over the Mach number range 1.2 to 3. The analysis coupled the Donnell shell equations with a linear piston theory to approximate the aerodynamic forces at the high supersonic Mach numbers while a slender body theory was used to approximate the aerodynamic forces at the low supersonic Mach numbers. The influence of the shell's structural boundary conditions and initial stresses on its aeroelastic stability was also investigated. This included a study of the shell stability around both its deformed and undeformed state, the deformed state being due to the initial stresses in the shell. The theoretical results were finally compared with recent experimental studies conducted at both the high and low supersonic Mach numbers. (Author).

Download or read book Dissertation Abstracts International written by and published by . This book was released on 1973 with total page 1064 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental Study on the Aeroelastic Stability of Thin Cylindrical Shells at the Lower Supersonic Mach Numbers written by Ronald O. Stearman and published by . This book was released on 1966 with total page 93 pages. Available in PDF, EPUB and Kindle. Book excerpt: During the initial phases of the test static pressure and boundary layer profile surveys were made over a rigid instrumented shell mounted in the position normally occupied by the flutter shells. The model boundary layer control system was also checked. In the final test phase the aeroelastic stability of five thin shells was investigated with the shells loaded under an axial compressive force and/or internal pressure. A highly divergent panel flutter instability occurred on all of the models tested, each shell being destroyed within less than a second. High speed motion pictures were taken during the flutter of three of the shells. These pictures revealed that the initial instability appeared either in the form of a local dimple or in the form of a wave traveling in the free stream direction. The characteristic wave lengths of these initial instabilities were small compared to the shell radius and length. A comparison of the present experimental results with some earlier studies conducted at the higher supersonic Mach numbers indicates that the critical ratio of dynamic pressure to bending stiffness required to induce flutter is approximately three times that found at the higher Mach numbers. Considerable disagreement was also observed between these experimental results and the results of two different theoretical analyses. (Author).

Download or read book OAR Research Review written by United States. Air Force. Office of Aerospace Research and published by . This book was released on 1968 with total page 528 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of the Aeroelastic Stability of Thin Cylindrical Shells at Subsonic Mach Numbers written by Warren E. White and published by . This book was released on 1971 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer and static-pressure data were obtained over a rigid pressure shell at Mach numbers from 0.6 to 0.9 and Reynolds numbers per foot from 300,000 to 5,300,000. These data were obtained with and without the addition of air injected into the boundary layer through a circular slot upstream of the test shell. Static aeroelastic characteristics of thin cylindrical shells were obtained at Mach number 0.9 without the use of boundary-layer control and without shell axial-force loading. An aeroelastic buckling failure was induced on all three shells by reducing the cavity pressure. Flutter of the shell was not encountered during the test. (Author).

Download or read book Research Review written by and published by . This book was released on 1969-11 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book American Doctoral Dissertations written by and published by . This book was released on 1998 with total page 784 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Research Review written by United States. Air Force. Office of Aerospace Research and published by . This book was released on 1969 with total page 346 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Experimental and Analytical Vibration Study of Elliptical Cylindrical Shells written by John L. Sewall and published by . This book was released on 1971 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper reports an experimental and analytical vibration study of free-free isotropic elliptical cylindrical shells of constant mass ranging in cross-sectional eccentricity from zero (circular shell) to 0.916. Experimental resonant frequencies, nodal patterns, and mode shapes were obtained by use of an air-jet shaker or an electrodynamic shaker with a noncontact inductance probe that could be moved over most of the shell surface. Experimental frequencies were in generally good agreement with analytical frequencies calculated by means of a Rayleigh-Ritz type of analysis featuring multiterm longitudinal and circumferential modal expansions. Frequencies for shells with eccentricity of 0.916 were as much as 40 percent below the corresponding circular-shell frequencies. As eccentricity increased, analytical and experimental mode shapes indicated considerable longitudinal and circumferential modal coupling.

Download or read book Some Recent Experimental Studies on the Aeroelastic Stability of Thin Cylindrical Shells Part I an Experimental Study of the Supersonic Flow Field Over an Aeroelastic Ogive Cylinder Model with Boundary Layer Control written by Philip L. Daily and published by . This book was released on 1970 with total page 153 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study was conducted as the first phase in a program to determine the influence of a compressible viscous boundary layer on cylindrical shell panel flutter. In the first part of the experiment, a study was conducted to provide data on the uniformity of the surface pressure distribution over the region of the flutter model where the thin cylindrical shells were mounted for the flutter experiments. The measured data confirmed that for all flow conditions above Mach Number 1.2, no significant pressure gradient existed over the region of the model where the flutter shells were mounted for testing. A study was then conducted to determine the effectiveness of the boundary layer control system for increasing the boundary layer thickness over the region of the model where the flutter shells were mounted. The boundary layer control system proved to be quite effective and under optimum conditions could increase the displacement and momentum thicknesses by a factor of 10. In general, the displacement and momentum thicknesses could be increased by at least 50% for most of the operating conditions of the wind tunnels by maximum activation of the boundary layer control systems. Finally boundary layer transition and profile similarity studies were conducted to determine the range of free stream flow conditions and boundary layer control activation rates where boundary layer profile similarity could be achieved over the test shell area of the model. The results indicate that similar laminar or turbulent boundary layer profiles can be maintained over the test region of the model for flow conditions where panel flutter can be expected to occur. (Author).

Download or read book Aeronautical Engineering written by and published by . This book was released on 1971 with total page 580 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)

Download or read book Nonlinear Vibrations and Stability of Shells and Plates written by Marco Amabili and published by Cambridge University Press. This book was released on 2008-01-14 with total page 391 pages. Available in PDF, EPUB and Kindle. Book excerpt: This unique book explores both theoretical and experimental aspects of nonlinear vibrations and stability of shells and plates. It is ideal for researchers, professionals, students, and instructors. Expert researchers will find the most recent progresses in nonlinear vibrations and stability of shells and plates, including advanced problems of shells with fluid-structure interaction. Professionals will find many practical concepts, diagrams, and numerical results, useful for the design of shells and plates made of traditional and advanced materials. They will be able to understand complex phenomena such as dynamic instability, bifurcations, and chaos, without needing an extensive mathematical background. Graduate students will find (i) a complete text on nonlinear mechanics of shells and plates, collecting almost all the available theories in a simple form, (ii) an introduction to nonlinear dynamics, and (iii) the state of art on the nonlinear vibrations and stability of shells and plates, including fluid-structure interaction problems.