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Flutter Experiences With Thin Pointed Tip Wings During Flight Tests Of Rocket Propelled Models At Mach Numbers From 08 To 195
Download Flutter Experiences With Thin Pointed Tip Wings During Flight Tests Of Rocket Propelled Models At Mach Numbers From 08 To 195 full books in PDF, epub, and Kindle. Read online Flutter Experiences With Thin Pointed Tip Wings During Flight Tests Of Rocket Propelled Models At Mach Numbers From 08 To 195 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Flutter Experiences with Thin Pointed-tip Wings During Flight Tests of Rocket-propelled Models at Mach Numbers from 0.8 to 1.95 by : Harvey A. Wallskog
Download or read book Flutter Experiences with Thin Pointed-tip Wings During Flight Tests of Rocket-propelled Models at Mach Numbers from 0.8 to 1.95 written by Harvey A. Wallskog and published by . This book was released on 1955 with total page 32 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 Supersonic Flutter of a 60 Degree Delta Wing Encountered During the Flight Test of a Rocket-propelled Model by : William T. Jr Lauten
Download or read book Supersonic Flutter of a 60 Degree Delta Wing Encountered During the Flight Test of a Rocket-propelled Model written by William T. Jr Lauten and published by . This book was released on 1954 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic Flutter Investigation of Models of Proposed Horizontal Tails for the X-15 Airplane by : Lou S. Young
Download or read book Transonic Flutter Investigation of Models of Proposed Horizontal Tails for the X-15 Airplane written by Lou S. Young and published by . This book was released on 1961 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Note on Flutter of a 60 Degree Delta Wing Encountered at Low-supersonic Speeds During the Flight of a Rocket-propelled Model by : William T. Lauten
Download or read book Note on Flutter of a 60 Degree Delta Wing Encountered at Low-supersonic Speeds During the Flight of a Rocket-propelled Model written by William T. Lauten and published by . This book was released on 1951 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis of the flight time history of a rocket-propelled model of a 60 degrees delta-wing airplane configuration, fired for the purpose of obtaining zero-lift drag data, indicated wing flutter and subsequent failure at low-supersonic Mach numbers. This flutter occurred during the unpowered decelerating portion of the flight. The behavior of the model during flight is discussed and the mass and stiffness characteristics of a duplicate wing are presented.
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 Description and Analysis of a Rocket-vehicle Experiment on Flutter Involving Wing Deformation and Body Motions by : H. J. Cunningham
Download or read book Description and Analysis of a Rocket-vehicle Experiment on Flutter Involving Wing Deformation and Body Motions written by H. J. Cunningham and published by . This book was released on 1950 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flight tests and a mathematical analysis were made to demonstrate and confirm a type of subsonic flutter involving rigid-body motions and wing deformations. For the configuration considered the period of the oscillation was approximately 100 chords per cycle which is well within the range of period found in dynamic-stability work on rigid aircraft with free controls. A mathematical analysis based on two-dimensional incompressible flow provided a conservative prediction of the airspeed at which the low-frequency flutter occurred. It was found that wing bending stiffness is the important parameter for preventing such flutter.
Book Synopsis Flutter Investigation of a True-speed Dynamic Model with Various Tip-tank Configurations by : John L. Sewall
Download or read book Flutter Investigation of a True-speed Dynamic Model with Various Tip-tank Configurations written by John L. Sewall and published by . This book was released on 1960 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 by : Robert S. Osborne
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 written by Robert S. Osborne and published by . This book was released on 1960 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 Overview of Recent Flight Flutter Testing Research at NASA Dryden by : Martin J. Brenner
Download or read book Overview of Recent Flight Flutter Testing Research at NASA Dryden written by Martin J. Brenner and published by . This book was released on 1997 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Proceedings of the 1958 Flight Flutter Testing Symposium by :
Download or read book Proceedings of the 1958 Flight Flutter Testing Symposium written by and published by . This book was released on 1975 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flutter of a 60 Degree Delta Wing (NACA 65A003 Airfoil) Encountered at Supersonic Speeds During the Flight Test of a Rocket-propelled Model by : Joseph H. Judd
Download or read book Flutter of a 60 Degree Delta Wing (NACA 65A003 Airfoil) Encountered at Supersonic Speeds During the Flight Test of a Rocket-propelled Model written by Joseph H. Judd and published by . This book was released on 1952 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free-flight Flutter Tests in the Transonic and Low Supersonic Speed Range of Three Low-aspect-ratio Swept, Tapered Wings on Rocket-propelled Vehicles by : William T. Lauten
Download or read book Free-flight Flutter Tests in the Transonic and Low Supersonic Speed Range of Three Low-aspect-ratio Swept, Tapered Wings on Rocket-propelled Vehicles written by William T. Lauten and published by . This book was released on 1956 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flutter data obtained by use of rocket-propelled vehicles in the transonic and low supersonic speed ranges for three low-aspect-ratio, highly-tapered, swept wings are presented herein. All three wings fluttered in the transonic range.
Book Synopsis Flutter Investigation of Models Having the Planform of the North American X-15 Airplane Wing Over a Range of Mach Numbers Form 0.56 to 7.3 by : Frederick W. Gibson
Download or read book Flutter Investigation of Models Having the Planform of the North American X-15 Airplane Wing Over a Range of Mach Numbers Form 0.56 to 7.3 written by Frederick W. Gibson and published by . This book was released on 1961 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flutter Model Tests of Advanced Wing Configurations at Initial Angles of Attack by : D. A. Brown
Download or read book Flutter Model Tests of Advanced Wing Configurations at Initial Angles of Attack written by D. A. Brown and published by . This book was released on 1964 with total page 127 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes an experimental and analytical program conducted to determine the transonic and supersonic flutter boundary of a highly swept, low aspect ratio lifting surface typical of re-entry vehicle configurations. Several semi-rigid flutter models were constructed and tested at Mach numbers from .4 to 1.2 and also at Mach numbers from 2.0 to 5.0. The effects on flutter speed of initial angle of attack, un-coupled frequency ratio, model thickness ratio and a tip surface normal to the plane of the basic model were determined. The model aspect ratio was .889, the leading edge sweep angle was 70 degrees and the thickness ratio of the basic model was 6%. Other thicknesses were 3% and 9%. The cross-section of the model was modified wedge having a wedge angle in the streamwise direction of 22 degrees 38 minutes. The trailing edge was blunt. (Author).
