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Unsteady Aerodynamics For Advanced Configurations
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Book Synopsis Unsteady Aerodynamics for Advanced Configurations by : H. T. Vivian
Download or read book Unsteady Aerodynamics for Advanced Configurations written by H. T. Vivian and published by . This book was released on 1965 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Equations for pressure distributions and generalized aerodynamic forces are derived for a thin nonplanar lifting surface in simple harmonic motion at subsonic speeds. A digital computer program, written in Fortran IV, is also presented. The computer program will generate up to a ten by ten matrix of generalized aerodynamic forces when given data for the geometry of a planar lifting surface with a folded planar tip, the flight Mach number, the reduced frequency of motion, and some control constants. Control surface deflections are not accounted for in this study.
Book Synopsis Unsteady Aerodynamics for Advanced Configurations by : H. T. Vivian
Download or read book Unsteady Aerodynamics for Advanced Configurations written by H. T. Vivian and published by . This book was released on 1965 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Unsteady Aerodynamics for Advanced Configurations by : E. R. Rodemich
Download or read book Unsteady Aerodynamics for Advanced Configurations written by E. R. Rodemich and published by . This book was released on 1965 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Unsteady Aerodynamics for Advanced Configurations. Part I. Application of the Subsonic Kernel Function to Nonplanar Lifting Surfaces by : H. T. VIVIAN
Download or read book Unsteady Aerodynamics for Advanced Configurations. Part I. Application of the Subsonic Kernel Function to Nonplanar Lifting Surfaces written by H. T. VIVIAN and published by . This book was released on 1965 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt: Equations for pressure distributions and generalized aerodynamic forces are derived for a thin nonplanar lifting surface in simple harmonic motion at subsonic speeds. A digital computer program, written in Fortran IV, is also presented. The computer program will generate up to a ten by ten matrix of generalized aerodynamic forces when given data for the geometry of a planar lifting surface with a folded planar tip, the flight Mach number, the reduced frequency of motion, and some control constants. Control surface deflections are not accounted for in the study. A kernel function method, which relates the pressure distribution to the downwash on a planar lifting surface, was extended and applied to a nonplanar lifting surface. Hsu's technique (PB-139 207) of employing Gaussian quadrature formulas is used when integrating the product of the kernal function and the lift function over the planform area. Recommendations are made to extend the method to account for blunted leading edges and the accompanying airfoil thickness and to account for control surface deflections. (Author).
Book Synopsis Unsteady Aerodynamics for Advanced Configurations by : T. C. Li
Download or read book Unsteady Aerodynamics for Advanced Configurations written by T. C. Li and published by . This book was released on 1965 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Unsteady Aerodynamics for Advanced Configurations by : Lowell V. Andrew
Download or read book Unsteady Aerodynamics for Advanced Configurations written by Lowell V. Andrew and published by . This book was released on 1968 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two methods were outlined in detail, and one of them was mechanized, for calculating acoustic ray paths emanating from any point in a non-uniform transonic flow field surrounding a wing. It gives the ray path, and the time, for the minimum time of travel from the acoustic source point to the field point. The resulting velocity potential is also computed. It was necessary to establish an accurate representation of the flow characteristics in the field surrounding the wing. Some ray lines travel over the planform and into the surrounding flow field. It was established that once off the planform they do not return. Available methods predict phase lags based on the assumption that acoustic rays travel in straight lines. The results of the study show this to be a very poor approximation at transonic speeds. Therefore, it is recommended that the method presented in the report be fully developed for the purpose of calculating generalized forces on wings in harmonic motion at transonic speeds. A computer program that would predict these phase lags with reasonable accuracy, and the corresponding flutter characteristics and unsteady aerodynamic loads on a wing responding to externally applied forces, such as gusts, would fill an important gap in the available technology. (Author).
Book Synopsis Unsteady Aerodynamics for Advanced Configurations by : E. Albano
Download or read book Unsteady Aerodynamics for Advanced Configurations written by E. Albano and published by . This book was released on 1965 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Unsteady Aerodynamics for Advanced Configurations by : M. T. Moore
Download or read book Unsteady Aerodynamics for Advanced Configurations written by M. T. Moore and published by . This book was released on 1965 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Unsteady Aerodynamics for Advanced Configurations by : M. T. Moore
Download or read book Unsteady Aerodynamics for Advanced Configurations written by M. T. Moore and published by . This book was released on 1966 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Unsteady Aerodynamics for Advanced Configurations. Part V. Unsteady Potential Flow Around Slender Bodies at Angles of Attack by : T. C. Li
Download or read book Unsteady Aerodynamics for Advanced Configurations. Part V. Unsteady Potential Flow Around Slender Bodies at Angles of Attack written by T. C. Li and published by . This book was released on 1965 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the portion of the study covered in this report, linearized theory is developed for potential flow around a slender body at not too large angles of attack. The solution is obtained by 'definitizing' the flow equation and rigorously satisfying the boundary conditions. This approach is completely different from conventional methods in that it constitutes a process of obtaining an analytic solution to the problem of potential flow by a 'march from the body' toward infinity. The extension of this new theory to the nonlinear case is immediate. Having shown it is possible to not restrict the Mach number, it is expected that the new theory should be applicable to the cases of subsonic, transonic and supersonic speeds as well. (Author).
Book Synopsis Unsteady Aerodynamics for Advanced Configurations. Part 2. a Transonic Box Method for Planar Lifting Surfaces by : E. R. Rodemich
Download or read book Unsteady Aerodynamics for Advanced Configurations. Part 2. a Transonic Box Method for Planar Lifting Surfaces written by E. R. Rodemich and published by . This book was released on 1965 with total page 121 pages. Available in PDF, EPUB and Kindle. Book excerpt: The fundamental equations of the transonic box method were derived, based on the representation of the velocity potential by a doublet distribution. They form the basis of a systematic method of treating an oscillating wing at M = 1, analogous to the supersonic Mach box method. A digital computer program, written in Fortran IV, is presented. The program applies to a planar wing of polygonal planform, with a straight trailing edge, and as many as three sweep angles along the leading edge. For a maximum of ten modes of oscillation, the program computes the oscillatory potentials and pressures and a generalized force matrix. Results obtained from the program are compared with existing theoretical and experimental values. Several possible extensions of the method are described.
Book Synopsis Unsteady Aerodynamics for Advanced Configurations. Part Iv. Application of the Supersonic Mach Box Method to Intersecting Planar Lifting Surfaces by : Michael T. Moore
Download or read book Unsteady Aerodynamics for Advanced Configurations. Part Iv. Application of the Supersonic Mach Box Method to Intersecting Planar Lifting Surfaces written by Michael T. Moore and published by . This book was released on 1965 with total page 141 pages. Available in PDF, EPUB and Kindle. Book excerpt: Ashley's approach to mutual interference theory by source superposition methods has been applied to the prediction of supersonic air loads on intersecting thin lifting surfaces in steady of oscillatory motion. Steady loading is regarded as the special case of zero frequency of oscillation. Each surface may be oscillating in a mode of rigid or elastic vibration or linear combinations thereof. Evvard's diaphragm concept has been extended to treat the out-of-plane interference problem. As a result, any leading or side edge on any of the intersecting surfaces may be subsonic. The study reported herein has lead to the formulation of a method by which diaphragm regions can be selected that eliminate the need for calculating out-of-plane velocity potentials. Based on mutual interference theory, the method requires only the calculation of out-of-plane velocities so that tangential flow conditions may be met. The Mach-box method has been used to obtain an approximate solution to the problem. In following the aerodynamic influence coefficient procedure of Zartarian and Hsu, each surface and diaphragm is overlaid with a grid of rectangular Mach boxes, the diagonals of which are parallel to the Mach lines. (Author).
Book Synopsis Unsteady Aerodynamics for Advanced Configurations. Part Iii. Elliptic-conical Wing in Linearized Unsteady Transonic Flow by : E. ALBANO
Download or read book Unsteady Aerodynamics for Advanced Configurations. Part Iii. Elliptic-conical Wing in Linearized Unsteady Transonic Flow written by E. ALBANO and published by . This book was released on 1965 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions were calculated for an elliptic cone performing plunging oscillations at sonic speed. The objective was to study the effect of blunt leading edges and wing thickness. Second order expressions in terms of the parameter (frequency times aspect ratio squared) for velocity potentials, pressure coefficients, and total lift and moment were derived using an iteration procedure and extended for unsteady transonic flow. The results indicate the possibility of developing simple formulas which will give accurate corrections throughout a wide speed range for the effects of leading-edge bluntness on airfoil pressure distributions. An extension of the analysis to account for pitching oscillations or to any flexible vibration mode, involving only chordwise deformations, would be straightforward but laborious. Also, one could treat without much additional difficulty planforms with curved leading edges. The possibility of treatment of flexible vibration modes, involving spanwise deformations, would depend upon successful evaluation of appropriate modifications of integrals contained in the report. (Author).
Book Synopsis Unsteady Aerodynamics by : Grigorios Dimitriadis
Download or read book Unsteady Aerodynamics written by Grigorios Dimitriadis and published by John Wiley & Sons. This book was released on 2024-03-11 with total page 581 pages. Available in PDF, EPUB and Kindle. Book excerpt: Unsteady Aerodynamics A comprehensive overview of unsteady aerodynamics and its applications The study of unsteady aerodynamics goes back a century and has only become more significant as aircraft become increasingly sophisticated, fly faster, and their structures are lighter and more flexible. Progress in the understanding of flow physics, computing power and techniques, and modelling technologies has led to corresponding progress in unsteady aerodynamics, with a wide range of methods currently used to predict the performance of engineering structures under unsteady conditions. Unsteady Aerodynamics offers a comprehensive and systematic overview of the application of potential and vortex methods to the subject. Beginning with an introduction to the fundamentals of unsteady flow, it then discusses the modelling of attached and separated, incompressible and compressible flows around two-dimensional and three-dimensional bodies. The result is an essential resource for design and simulation in aerospace engineering. Unsteady Aerodynamics readers will also find: MATLAB examples and exercises throughout, with codes and solutions on an accompanying website Detailed discussion of most classes of unsteady phenomena, including flapping flight, transonic flow, dynamic stall, flow around bluff bodies and more Validation of theoretical and numerical predictions using comparisons to experimental data from the literature Unsteady Aerodynamics is ideal for researchers, engineers, and advanced students in aerospace engineering.
Book Synopsis Unsteady Aerodynamic Pressures in Transonic Flow by : L. V. Andrew
Download or read book Unsteady Aerodynamic Pressures in Transonic Flow written by L. V. Andrew and published by . This book was released on 1971 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: Oscillatory pressures as well as total loads were obtained on a 70-degree delta-wing model undergoing sinusoidal pitch rotation in transonic flow. The mach number range was from 0.8 to 1.2, and the maximum reduced frequency (based on centerline half chord) achieved was 0.172. Corresponding pressures were computer using the kernel function method and the doublet/vortex lattice method at subsonic speeds, the sonic box method, and the supersonic mach box method. Both box methods produce point values of potentials that are fitted by surfaces tyo yeld pressures. Comparisomns of the measured and computer pressures show that, in general (and as expected), the computed pressures are higher than the measured values near the leading edge. Also, in general (but unexpected), the computed phase lags between motion of the surface and the pressures generated by the motion are lower than the measure values.
Download or read book The NASTRAN Theoretical Manual written by and published by . This book was released on 1981 with total page 946 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Papers Presented at the Symposium on Unsteady Aerodynamics by :
Download or read book Papers Presented at the Symposium on Unsteady Aerodynamics written by and published by . This book was released on 1971 with total page 356 pages. Available in PDF, EPUB and Kindle. Book excerpt:
