Download or read book Mathematical Methods of Airfoil Design written by Alexander M. Elizarov and published by Wiley-VCH. This book was released on 1997-07-15 with total page 300 pages. Available in PDF, EPUB and Kindle. Book excerpt: Devoted to the theory of aerodynamic design of subsonic airfoils. It presents the results of more than thirty years research in Russia as well as research by new authors. The state-of-the-art situation in this theory is fully reflected.

Download or read book Airfoil Design and Data written by Richard Eppler and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 569 pages. Available in PDF, EPUB and Kindle. Book excerpt: This detailed book describes a procedure for the design and analysis of subsonic airfoils. Contains 116 new airfoils for a wide range of Reynolds numbers and application requirements, including the input data for the computer code.

Download or read book Mathematical Methods in Aerodynamics written by Lazãr Dragos and published by Springer Science & Business Media. This book was released on 2003 with total page 626 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book provides a solid and unitary mathematical foundation of the basic and advanced principles of aerodynamics. The densities of the fundamental solutions are determined from singular integral equations. The fundamental solutions method in aerodynamics was considered for the first time and used by the author in over 30 papers published in prestigious journals (e.g. QAM, AIAA, ZAMM, etc) in order to develop a unitary theory. The boundary element method is used for numerical approximations in compressible aerodynamics. The text incorporates several original contributions, among other traditional mathematical methods. The book also represents a comprehensive presentation of research results since the seminal books on aerodynamics of Ashley and Landahl (1965) and Katz & Plotkin (1991). A rigorous mathematical approach is used to present and explain classic and modern results in this field of science. The author has therefore conceived several appendices on the Distribution Theory, the singular Integral Equations Theory, the Finite Part, Gauss Quadrature Formulae, etc. The book is concluded by a relevant bibliographical list which is especially useful for researchers. The book is aimed primarily at applied mathematicians, aeronautical engineers and space science researchers. The text may be used also as a comprehensive introduction to the mathematical foundations fo aerodynamics, by graduate students n engineering and fluid dynamics with a strong mathematical background.

Download or read book Airfoil Design by an All At Once Method written by and published by . This book was released on 1997 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt: The all-at-once approach is implemented to solve an optimum airfoil design problem. The airfoil design problem is formulated as a constrained optimization problem in which flow variables and design variables are viewed as independent and the coupling steady state Euler equation is included as a constraint, along with geometry and other constraints. In this formulation, the optimizer computes a sequence of points which tend toward feasiblility and optimality at the same time (all-at-once). This decoupling of variables typically makes the problem less nonlinear and can lead to more efficient solutions. In this paper an existing optimization algorithm is combined with an existing flow code. The problem formulation, its discretization, and the underlying solvers are described. Implementation issues are presented and numerical results are given which indicate that the cost of solving the design problem is approximately six times the cost of solving a single analysis problem.

Download or read book MATHEMATICAL MODELING OF WING SECTIONS written by Boris Dolomanov and published by Xlibris Corporation. This book was released on 2012-05-09 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: About the Brochure Dear reader! This brochure IS all about the Method of mathematical modeling of wing sections. It is meant for professionals who work on design wings and also blades of propellers or turbines, rudders or any objects that have airfoil in section. The author devoted many years to develop this Method and now brings it to your attention. When creating this Method, the author tried to make the description simple, avoid complex theoretical structures, strived to convey the main ideas briefly and understandable to anyone who has technical college or university background. If the reader would like to send their comments on discussed points or report typos, inaccuracies and so on, the author will appreciate. Please send all comments, Email: [email protected] Boris Dolomanov

Download or read book Special Course on Inverse Methods for Airfoil Design for Aeronautical and Turbomachinery Applications written by and published by . This book was released on 1990 with total page 564 pages. Available in PDF, EPUB and Kindle. Book excerpt: "This lecture series is devoted to major aspects of aerofoil design both for aeronautical and turbomachine application. These include: (1) optimisation of target pressure and velocity distribution. Both direct optimisation resulting from an inverse boundary layer calculation and an iterative optimisation of the loses are presented. (2) aerofoil design by means of inverse methods. This ranges from simple parametric definitions of two- dimensional cross sections to a detailed numerical definition of three dimensional shapes. blade or airfoil designs are normally made in two steps, and the lectures are accordingly grouped into two parts. First, optimisation of target pressure and velocity distributions are discussed taking into account the required performance and the lost mechanisms in the boundary layer. Both direct optimisation resulting from an inverse boundary layer calculation, and an iterative optimisation by minimisation of the losses are presented. It is clear from both procedures that inclusion of off-design operation is one of the greatest difficulties involved in blade or airfoil operation. The second part gives an overview of the numerous inverse blade design methods that have been developed both for turbomachinery and aeronautical applications. This ranges from simple parameter definitions of two-dimensional cross-sections to the full three-dimensional definition of wings and blade channels."--DTIC.

Download or read book Aircraft Aerodynamic Design with Computational Software written by Arthur Rizzi and published by Cambridge University Press. This book was released on 2021-05-20 with total page 467 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic design of aircraft presented with realistic applications, using CFD software. Tutorials, exercises, and mini-projects provided involve design of real aircraft. Using online resources and supplements, this text prepares last-year undergraduates and first-year graduate students for industrial aerospace design and analysis tasks.

Download or read book A Multi point Inverse Airfoil Design Method Based on Conformal Mapping written by Michael S. Selig and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Theory of Supercritical Wing Sections with Computer Programs and Examples written by F. Bauer and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 218 pages. Available in PDF, EPUB and Kindle. Book excerpt: At present, there is considerable interest in supercritical wing technology for the development of aircraft designed to fly near the speed of sound. The basic principle is the suppression of boundary layer separation by shifting the shock waves that occur on the wing toward the trailing edge and making them as weak as possible. The purpose of this report is to make available to the engineering public mathematical methods for the design of supercritical wings. These methods depend on the numerical solution of the partial differential equations of two-dimensional gas dynamics. The main contribution is a computer program for the design of shockless transonic airfoils using the hodograph transformation and analytic continuation into the complex domain. Another contribution is a program for the analysis of transonic flow with shocks past an airfoil at off-design conditions. In our design work we include a turbulent boundary layer correction. Part I of the paper is devoted to a description of the mathemati cal theory and need not be studied by those primarily concerned with running the programs. Part II is a manual for users of our programs which is independent of the theoretical part. In Part III and in Appendices II and III we give numerical examples and discuss computa tional results. The main substance of the report, however, is contained in the listing of the computer programs themselves in Appendix IV. We have used the Fortran language throughout and we have included numerous comment cards in the listing.

Download or read book Shock Free Transonic Airfoil Design by a Hodograph Method written by William Zeitler Strang and published by . This book was released on 1984 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: Refined mathematical methods are required for the analytical solution of the partial differential equation governing steady, two-dimensional, compressible, transonic, potential fluid flow. This equation is nonlinear in the physical plane and so does not lend itself to standard analytical solution methods. The Molenbroek-Chaplygin transformation, where the physical Cartesian coordinates as the independent variables are replaced by the velocity magnitude and direction as the independent variables, linearizes the governing equation which may then be analytically solved. The plane where the said velocity parameters are the independent variables is termed the hodograph plane. Likewise, the transformed differential equation is known as the hodograph equation and it is solved by hodograph methods. This mathematical study addresses the solution of transonic flow phenomena by an extension of Lighthill's hodograph method. Lighthill's method transforms a given solution of the Laplace equation into a solution of the hodograph equation for subsonic flows only. A new relation is developed in this study extending this transformation technique to include flows up to March 2.2735 in air. Requiring only numerical data concerning the velocity field, this hodograph method is computationally efficient and mathematically straightforward.

Download or read book Applied Mathematical Methods written by Dasgupta, Bhaskar and published by Pearson Education India. This book was released on 2006 with total page 524 pages. Available in PDF, EPUB and Kindle. Book excerpt: Applied Mathematical Methods covers the material vital for research in today's world and can be covered in a regular semester course. It is the consolidation of the efforts of teaching the compulsory first semester post-graduate applied mathematics course at the Department of Mechanical Engineering at IIT Kanpur in two successive years.

Download or read book Mathematical Methods in Aerodynamics written by Lazãr Dragos and published by Springer. This book was released on 2004-03-14 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The researchers in Aerodynamics know that there is not a unitary method of investigation in this field. The first mathematical model of the air plane wing, the model meaning the integral equation governing the phe nomenon, was proposed by L. Prandtl in 1918. The integral equation deduced by Prandtl, on the basis of some assumptions which will be specified in the sequeL furnishes the circulation C(y) (see Chapter 6). U sing the circulation, one calculates the lift and moment coefficients, which are very important in Aerodynamics. The first hypothesis made by Prandtl consists in replacing the wing by a distribution of vortices on the plan-form D of the wing (i. e. the projection of the wing on the plane determined by the direction of the uniform stream at infinity and t he direction of the span of the wing). Since such a distribution leads to a potential flow in the exterior of D and the experiences show that downstream the flow has not this character, Prandtl introduces as a sup plementary hypothesis another vortices distribution on the trace of the domain D in the uniform stream. The first kind of vortices are called tied vortices and the second kind of vortices are called free vortices.

Download or read book Low Reynolds Number Aerodynamics written by Thomas J. Mueller and published by Springer Science & Business Media. This book was released on 2013-03-08 with total page 456 pages. Available in PDF, EPUB and Kindle. Book excerpt: Current interest in a variety of low Reynolds number applications has focused attention on the design and evaluation of efficient airfoil sections at chord Reynolds numbers from about 100,000 to about 1,000,000. These applications include remotely piloted vehicles (RPVs) at high altitudes, sailplanes, ultra-light man-carrying/man powered aircraft, mini-RPVs at low altitudes and wind turbines/propellers. The purpose of this conference was to bring together those researchers who have been active in areas closely related to this subject. All of the papers presented are research type papers. Main topics are: Airfoil Design and Analysis, Computational Studies, Stability and Transition, Laminar Separation Bubble, Steady and Unsteady Wind Tunnel Experiments and Flight Experiments.

Download or read book Enhancements to the Inverse Design of Low Speed Natural Laminar Flow Airfoils written by and published by . This book was released on 2003 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of inverse airfoil design has traditionally been the determination of the airfoil shape that results in desired aerodynamic characteristics. Under this general classification, inverse methods have progressed a great deal over the past few decades. With modern inverse methods, it is possible to prescribe velocity and/or boundary-layer characteristics along with desired geometric constraints in the design of airfoils. In spite of these advances, inverse airfoil design still involves a certain amount of trial and error when a designer attempts to fine tune the drag polar of the airfoil or when attempting to tailor the airfoil for a particular application. The research presented in this thesis makes two specific advances to the state of the art in inverse design. The first part of the research describes the development of an approach by which a desired boundary-layer transition curve can be specified as an input to inverse design. The second part presents an approach for incorporating aircraft performance considerations in the inverse design process. The two advances can help reduce the design cycle time for airfoil and aircraft design by reducing the amount of trial and error in the design process. The motivation factor for the first part of the research (inverse design via specification of the boundary-layer transition curve) was the strong connection between the transition curve and the airfoil drag polar. In the approach developed, a multidimensional Newton iteration is used to adjust the velocity distribution until the transition lift coefficient at several locations on the airfoil are within a given tolerance of the specifications. It is shown that the shape of the drag bucket as well as the camber and extents of laminar flow on the airfoil can be controlled through the specification of the transition-curve. This method represents an enhancement over previous inverse airfoil design methods since it allows for a single specification that spans multipl.

Download or read book Mathematical Methods in Fluid Mechanics written by and published by . This book was released on 1980 with total page 672 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Design of Axial flow Compressors written by Lewis Research Center and published by . This book was released on 1965 with total page 542 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Control Theory Based Airfoil Design Using the Euler Equations written by Antony Jameson and published by . This book was released on 1994 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: "This paper describes the implementation of optimization techniques based on control theory for airfoil design. In our previous work [9, 10, 15] it was shown that control theory could be employed to devise effective optimization procedures for two-dimensional profiles by using the potential flow equation with either a conformal mapping or a general coordinate system. The goal of our present work is to extend the development to treat the Euler equations in two-dimensions by procedures that can readily be generalized to treat complex shapes in three-dimensions. Therefore, we have developed methods which can address airfoil design through either an analytic mapping or an arbitrary grid perturbation method applied to a finite volume discretization of the Euler equations. Here the control law serves to provide computationally inexpensive gradient information to a standard numerical optimization method. Results are presented for both the inverse problem and drag minimization problem."