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An Experimental Investigation Of The Flutter Of Several Wings Of Varying Aspect Ratio Density And Thickness Ratio At Mach Numbers From 060 To 110
Download An Experimental Investigation Of The Flutter Of Several Wings Of Varying Aspect Ratio Density And Thickness Ratio At Mach Numbers From 060 To 110 full books in PDF, epub, and Kindle. Read online An Experimental Investigation Of The Flutter Of Several Wings Of Varying Aspect Ratio Density And Thickness Ratio At Mach Numbers From 060 To 110 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis AN EXPERIMENTAL INVESTIGATION OF THE FLUTTER OF SEVERAL WINGS OF VARYING ASPECT RATIO, DENSITY, AND THICKNESS RATIO AT MACH NUMBERS FROM 0.60 TO 1.10 by :
Download or read book AN EXPERIMENTAL INVESTIGATION OF THE FLUTTER OF SEVERAL WINGS OF VARYING ASPECT RATIO, DENSITY, AND THICKNESS RATIO AT MACH NUMBERS FROM 0.60 TO 1.10 written by and published by . This book was released on 1954 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Effect of Aspect Ratio and Mach Number on the Flutter of Cantilever Wings by :
Download or read book Experimental Investigation of the Effect of Aspect Ratio and Mach Number on the Flutter of Cantilever Wings written by and published by . This book was released on 1960 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flutter Investigation of Two Thin, Low-aspect-ratio, Swept, Solid, Metal Wings in the Transonic Range by Use of Free-falling Body by : W. T. Lauten
Download or read book Flutter Investigation of Two Thin, Low-aspect-ratio, Swept, Solid, Metal Wings in the Transonic Range by Use of Free-falling Body written by W. T. Lauten and published by . This book was released on 1952 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Effect of Aspect Ratio and Mach Number on the Flutter of Cantilever Wings by : Jr. E. Widmayer
Download or read book Experimental Investigation of the Effect of Aspect Ratio and Mach Number on the Flutter of Cantilever Wings written by Jr. E. Widmayer and published by . This book was released on 1950 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Wing Flutter at Transonic Speeds for Six Systematically Varied Wing Plan Forms by : George W. Jones
Download or read book Investigation of Wing Flutter at Transonic Speeds for Six Systematically Varied Wing Plan Forms written by George W. Jones and published by . This book was released on 1953 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Results of Two Experiments on Flutter of High-aspect-ratio Swept Wings in the Transonic Speed Range by : William T. Lauten
Download or read book Results of Two Experiments on Flutter of High-aspect-ratio Swept Wings in the Transonic Speed Range written by William T. Lauten and published by . This book was released on 1952 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flutter at Very High Speeds by : Harry L. Runyan
Download or read book Flutter at Very High Speeds written by Harry L. Runyan and published by . This book was released on 1957 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Flutter Characteristics of Swept Wings at Transonic Speeds by : Laurence K. Loftin
Download or read book Flutter Characteristics of Swept Wings at Transonic Speeds written by Laurence K. Loftin and published by . This book was released on 1955 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Effects of Density and Mach Number on the Flutter Speed of Two Uniform Wings by : George E. Castile
Download or read book Some Effects of Density and Mach Number on the Flutter Speed of Two Uniform Wings written by George E. Castile and published by . This book was released on 1949 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Present-day trends toward flight at high speeds and high altitudes have led to increasing interest in the flutter speed at low densities and high Mach numbers. An experimental investigation has consequently been made to determine some of the effects of these parameters on flutter speed.
Book Synopsis Investigation of Transonic Flutter Characteristics of a Thin 10 Degree Sweptback Wing Having an Aspect Ratio of 4 and a Taper Ratio of 0.6 by : George W. Jones
Download or read book Investigation of Transonic Flutter Characteristics of a Thin 10 Degree Sweptback Wing Having an Aspect Ratio of 4 and a Taper Ratio of 0.6 written by George W. Jones and published by . This book was released on 1957 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.79 and 1.34 on a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6. The data obtained have been compared with data from NACA Research Memorandum L55I13A for zero and 30 degree sweptback wings of the type investigated, the flutter boundary for the 10 degree sweptback wing falls between those for the zero degree and 30 degree sweptback wings in the low supersonic Mach number range. However, the subsonic level (around a Mach number of 0.8) of the flutter boundary for the 10 degree sweptback wing lies above those for the zero and 30 degree sweptback wings. In addition, the amount of rise in the flutter boundary from the subsonic level to the supersonic values is about the same for the wings with angles of sweepback of 10 degrees and zero degrees, but is much greater for the wing with an angle of sweepback of 30 degrees.
Book Synopsis A Study of Several Factors Affecting the Flutter Characteristics Calculated for Two Swept Wings by Piston Theory and by Quasi-steady Second-order Theory and Comparison with Experiments by : Robert Merrill Bennett
Download or read book A Study of Several Factors Affecting the Flutter Characteristics Calculated for Two Swept Wings by Piston Theory and by Quasi-steady Second-order Theory and Comparison with Experiments written by Robert Merrill Bennett and published by . This book was released on 1963 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Compilation of Experimental Flutter Information by : H. J. Cunningham
Download or read book A Compilation of Experimental Flutter Information written by H. J. Cunningham and published by . This book was released on 1954 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Effects of Sweep and Aspect Ratio on the Transonic Flutter Characteristics of a Series of Thin Cantilever Wings Having a Taper Ratio of 0.6 by : John R. Unangst
Download or read book Some Effects of Sweep and Aspect Ratio on the Transonic Flutter Characteristics of a Series of Thin Cantilever Wings Having a Taper Ratio of 0.6 written by John R. Unangst and published by . This book was released on 1963 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Flutter Experiments at a Mach Number of 1.3 on Cantilever Wings with a Tubular and Closed Bodes at the Tips by : John Locke McCarty
Download or read book Some Flutter Experiments at a Mach Number of 1.3 on Cantilever Wings with a Tubular and Closed Bodes at the Tips written by John Locke McCarty and published by . This book was released on 1953 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flutters tests of 39 cantilever wings with tubular bodies or closed bodies at the tips have been made in a small intermittent-flow supersonic wind tunnel where the testing technique involved changing the structural parameters so that the combinations would flutter at the tunnel Mach number of 1.3. Some effects of mass moment of inertia of the tube about the elastic axis, tube center-of-gravity location, and mass flow through the tube on the flutter-speed coefficient were studied. The experimental results are compared with a theory using two-dimensional air forces on the wing and tube forces derived form a modified slender body theory.
Book Synopsis Preliminary Study of Some Factors which Affect the Stall-flutter Characteristics of Thin Wings by : A. Gerald Rainey
Download or read book Preliminary Study of Some Factors which Affect the Stall-flutter Characteristics of Thin Wings written by A. Gerald Rainey and published by . This book was released on 1952 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Some of the other factors considered were found to be more or less significant however, all the factors will require further study if their effects are to be more fully interpreted.
Book Synopsis Initial Experiments on Flutter of Unswept Cantilever Wings at Mach Number 1.3 by : W. J. Tuovila
Download or read book Initial Experiments on Flutter of Unswept Cantilever Wings at Mach Number 1.3 written by W. J. Tuovila and published by . This book was released on 1954 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt: A supersonic tunnel designed to operate at Mach number 1.3 was used for a preliminary experimental flutter investigation of widely different unswept cantilever wings. Data for 12 wings with mass-density parameters 1(k) ranging from 52 to 268, center-of-gravity positions ranging from 46 to 63 percent chord from the leading edge, and elastic-axis positions ranging from 34 to 52 percent chord from the leading edge are considered.
