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Experimental Determination Of The Pressure Distribution On A Rectangular Wing Oscillating In The First Bending Mode For Mach Numbers From 024 To 130
Download Experimental Determination Of The Pressure Distribution On A Rectangular Wing Oscillating In The First Bending Mode For Mach Numbers From 024 To 130 full books in PDF, epub, and Kindle. Read online Experimental Determination Of The Pressure Distribution On A Rectangular Wing Oscillating In The First Bending Mode For Mach Numbers From 024 To 130 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Experimental Determination of the Pressure Distribution on a Rectangular Wing Oscillating in the First Bending Mode for Mach Numbers from 0.24 to 1.30 by : Henry C. Lessing
Download or read book Experimental Determination of the Pressure Distribution on a Rectangular Wing Oscillating in the First Bending Mode for Mach Numbers from 0.24 to 1.30 written by Henry C. Lessing and published by . This book was released on 1960 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Aerodynamic Pressures on a Harmonically Oscillating Rectangular Wing by : John Lewis Troutman
Download or read book The Aerodynamic Pressures on a Harmonically Oscillating Rectangular Wing written by John Lewis Troutman and published by . This book was released on 1960 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Measurement of the Static Aeroelastic Deformation and Loading of a Wing in Supersonic Flow by : Frank Herman Durgin
Download or read book A Measurement of the Static Aeroelastic Deformation and Loading of a Wing in Supersonic Flow written by Frank Herman Durgin and published by . This book was released on 1963 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aeroelastic analysis of Zisfein, Donato and Farrell (AD-155739) uses an aerodynamic matrix, a structural matrix and the initial angle of attack to predict the equilibrium pressures and shape of a wing. To test the accuracy of their methods, a flexible wing was built and instrumented with pressure taps and mirrors. The wing was tested at Mach numbers of 2 and 3, and both the pressure distribution and the deflected shape were measured. An aerodynamic matrix computed on the basis of the semiempirical procedures of the above authors was used to predict pressure distributions, and an experimentally determined structural matrix was used to find equilibrium angles of attack. Finally, these two matrices were used in the aeroelastic equations to compute pressures and angles of attack from the undeflected shape of the wing. Comparisons between theory and experiment are presented for eight different free stream conditions. -- page iii.
Book Synopsis Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9 by : Barry Moskowitz
Download or read book Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9 written by Barry Moskowitz and published by . This book was released on 1951 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Pressure distributions on two wing-body combinations were obtained at Mach number of 1.9 to investigate wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body having an ogive nose were investigated alone and in combination. Pressure distributions over the wing body combination compared favorable with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of wings where boundary layer of body modified the flow.
Book Synopsis Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges by : Julio Chu
Download or read book Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges written by Julio Chu and published by . This book was released on 1996 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Aspect Ratio on Undamped Torsional Oscillations of a Thin Rectangular Wing in Supersonic Flow by : Charles E. Watkins
Download or read book Effect of Aspect Ratio on Undamped Torsional Oscillations of a Thin Rectangular Wing in Supersonic Flow written by Charles E. Watkins and published by . This book was released on 1949 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: The velocity potential and aerodynamic-torsional moment coefficients based on the linearized equations of motion for small disturbances are derived for a rectangular wing by means of appropriate distributions of moving sources and doublets. The aerodynamic-torsional-moment coefficent to study the effect of aspect ratio on the undamped torsional oscillations of a finite rectangular wing. Decreasing the aspect ratio of the wing is found to have a highly stabilizing effect on the undamped torsional oscillations. The results of some selected calculations are presented in the figures that illustrate this fact.
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 Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 by : Peter T. Bernot
Download or read book Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 written by Peter T. Bernot and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Oscillating Pressures Near a Static Pusher Propeller at Tip Mach Numbers Up to 1.20 with Special Reference to the Effects of the Presence of the Wing by : Harvey H. Hubbard
Download or read book Oscillating Pressures Near a Static Pusher Propeller at Tip Mach Numbers Up to 1.20 with Special Reference to the Effects of the Presence of the Wing written by Harvey H. Hubbard and published by . This book was released on 1954 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of free-space oscillating presssures near a static propeller in the region where a wing might be located are presented for the tip Mach number range of 0.50 to 1.20 and these results are compared with available theory. Some measurements are also presented which were made near the tipes in the region where a fuselage might be located in order to extend the range of existing data from a tip Mach number of 1.00 to 1.20. In addition to a description of the free-space pressure field, meausrements are given from some of the same field points with a wing in place.
Book Synopsis Theoretical and Experimental Pressure Distributions on Low Aspect Ratio Wings Oscillating in an Incompressible Flow by : William R. Laidlaw
Download or read book Theoretical and Experimental Pressure Distributions on Low Aspect Ratio Wings Oscillating in an Incompressible Flow written by William R. Laidlaw and published by . This book was released on 1954 with total page 426 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow by : Mitchel H. Bertram
Download or read book An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow written by Mitchel H. Bertram and published by . This book was released on 1963 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented for a study of the pressure and heat-transfer distributions and force characteristics of slab delta wings of 70° sweep at Mach numbers of 6.8 and 9.6 in air and 18 in helium. The wings had cylindrical leading edges and were tested with two different noses. One was sharp in plan view and the other was a tangent sphere with the same diameter as the cylindrical leading edge. Simple approaches to predicting the heat transfer are shown to be successful if the flow pattern peculiar to the angle-of-attack range under consideration is taken into account.
Book Synopsis Flight Investigation at Mach Numbers from 0.6 to 1.7 to Determine Drag and Base Pressures on a Blunt-trailing-edge Airfoil and Drag of Diamond and Circular-arc Airfoils at Zero Lift by : John D. Morrow
Download or read book Flight Investigation at Mach Numbers from 0.6 to 1.7 to Determine Drag and Base Pressures on a Blunt-trailing-edge Airfoil and Drag of Diamond and Circular-arc Airfoils at Zero Lift written by John D. Morrow and published by . This book was released on 1950 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models having rectangular 6-percent-thick wings are presented for a Mach number range of 0.6 to 1.7. Wings of aspect ratio 2.7 having diamond, circular-arc, and blunt-trailing edge airfoil sections were tested. Pressures were measured on the base of the blunt-trailing-edge airfoil which had a rectangular section with a 40-percent-chord beveled leading edge. Although the blunt-trailing-edge airfoil had high drag throughout the Mach number range investigated, because of high base suction pressures, it is believed that the data presented can be used in the design of more nearly optimum blunt-base airfoils. Of the airfoils tested the circular-arc section had lowest drag at high-subsonic speeds, and the diamond section had lowest drag at supersonic speeds.
Book Synopsis Transonic Pressure Distributions on a Rectangular Supercritical Wing Oscillating in Pitch by :
Download or read book Transonic Pressure Distributions on a Rectangular Supercritical Wing Oscillating in Pitch written by and published by . This book was released on 1983 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges by : Julio Chu
Download or read book Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges written by Julio Chu and published by . This book was released on 1996 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aeronautical Engineer's Data Book by : Cliff Matthews
Download or read book Aeronautical Engineer's Data Book written by Cliff Matthews and published by Elsevier. This book was released on 2001-10-17 with total page 288 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aeronautical Engineer's Data Bookis an essential handy guide containing useful up to date information regularly needed by the student or practising engineer. Covering all aspects of aircraft, both fixed wing and rotary craft, this pocket book provides quick access to useful aeronautical engineering data and sources of information for further in-depth information. Quick reference to essential data Most up to date information available
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1991 with total page 296 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Future Space-Transport-System Components under High Thermal and Mechanical Loads by : Nikolaus A. Adams
Download or read book Future Space-Transport-System Components under High Thermal and Mechanical Loads written by Nikolaus A. Adams and published by Springer Nature. This book was released on 2020-10-26 with total page 409 pages. Available in PDF, EPUB and Kindle. Book excerpt: This open access book presents the findings of Collaborative Research Center Transregio 40 (TRR40), initiated in July 2008 and funded by the German Research Foundation (DFG). Gathering innovative design concepts for thrust chambers and nozzles, as well as cutting-edge methods of aft-body flow control and propulsion-component cooling, it brings together fundamental research undertaken at universities, testing carried out at the German Aerospace Center (DLR) and industrial developments from the ArianeGroup. With a particular focus on heat transfer analyses and novel cooling concepts for thermally highly loaded structures, the book highlights the aft-body flow of the space transportation system and its interaction with the nozzle flow, which are especially critical during the early phase of atmospheric ascent. Moreover, it describes virtual demonstrators for combustion chambers and nozzles, and discusses their industrial applicability. As such, it is a timely resource for researchers, graduate students and practitioners.
