Josef Rom

High Angle of Attack Aerodynamics (eBook, PDF)

Subsonic, Transonic, and Supersonic Flows

• Format: PDF

Produktbeschreibung

The aerodynamics of aircraft at high angles of attack is a subject which is being pursued diligently, because the modern agile fighter aircraft and many of the current generation of missiles must perform well at very high incidence, near and beyond stall. However, a comprehensive presentation of the methods and results applicable to the studies of the complex aerodynamics at high angle of attack has not been covered in monographs or textbooks. This book is not the usual textbook in that it goes beyond just presenting the basic theoretical and experimental know-how, since it contains reference material to practical calculation methods and technical and experimental results which can be useful to the practicing aerospace engineers and scientists. It can certainly be used as a text and reference book for graduate courses on subjects related to high angles of attack aerodynamics and for topics related to three-dimensional separation in viscous flow courses. In addition, the book is addressed to the aerodynamicist interested in a comprehensive reference to methods of analysis and computations of high angle of attack flow phenomena and is written for the aerospace scientist and engineer who is familiar with the basic concepts of viscous and inviscid flows and with computational methods used in fluid dynamics.

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Produktdetails

• Verlag: Springer US
• Seitenzahl: 399
• Erscheinungstermin: 6. Dezember 2012
• Englisch
• ISBN-13: 9781461228240
• Artikelnr.: 43987549

Inhaltsangabe

1 Introduction.- 2 Description of Flows at High Angles of Attack.- 2.1. The Finite Lifting Wing of Medium and High AR at Low Subsonic Speeds.- 2.2. The Low AR Rectangular Wing at Low Subsonic Speeds.- 2.3. The Slender Delta Type Wings.- 2.4. The Flow Over Elongated Slender Bodies.- 2.5. Aircraft Type Configurations.- 2.6. Vortex Breakdown.- 2.7. Nonsteady Aerodynamics at High Angles of Attack on Slender Configurations.- 2.8. Effect of Separation at High Angles of Attack in Hypersonic Flows.- References.- 3 The Topology of Separating and Reattaching Vortical Flows.- 3.1. Equations for Vortical Flows.- 3.2. Topological Concepts for the Analysis of Vortical Flows.- References.- 4 Linear Aerodynamics of Wings and Bodies.- 4.1. Equations for Potential Subsonic Flows.- 4.2. Equations for the Lifting Wing at Low Speeds.- 4.3. The Linear Panel Methods for the Calculation of the Subsonic Aerodynamic Coefficients for Wings and Bodies.- 4.4. Low and High Order Linear Panel Methods for Subsonic and Supersonic Flows.- 4.5. Comparison of the Various Panel Methods.- References.- 5 Vortex Flows and the Rolled Up Vortex Wake.- 5.1. Vortex Core of the Rolled Up Wake.- 5.2. The Rolled Up Tip Vortices.- 5.3. The Rolling-Up of the Vortex Wake Behind Wings.- 5.4. The "Bursting" of the Rolled Up Vortices.- References.- 6 Nonlinear Aerodynamics of Wings and Bodies at High Angles of Attack.- 6.1. Analytical and Semi-Empirical Methods for Calculations of the Nonlinear Aerodynamic Characteristics.- References.- 7 The Nonlinear Panel Methods for Aircraft and Missile Configurations at High Angles of Attack.- 7.1. The Nonlinear Vortex Lattice Method (NLVLM) for Subsonic Flows.- 7.2. The Free Vortex Sheet (FVS) Method for Subsonic Flows.- 7.3. The NLVLM for Supersonic Flow.- References.- 8Solutions of the Euler Equations for Flows over Configurations at High Angles of Attack.- 8.1. The Euler Equations.- 8.2. Numerical Methods of Solution of the Euler Equations.- References.- 9 Solutions to the Navier-Stokes Equations for Flows over Configurations at High Angles of Attack.- 9.1. Formulation of the Navier-Stokes Equations.- 9.2. Numerical Methods for Solutions of the Navier-Stokes Equations.- 9.3. Method of solution of the Thin-Layer Equations.- 9.4. Grid Topology, Boundary and Initial Conditions.- 9.5. Solutions of the Navier-Stokes Equations for Flows over Three-Dimensional Configurations at High Angles of Attack.- References.- Credits.- Author Index.