Computation Of Supersonic Flow Over Flying Configurations
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Computation of Supersonic Flow over Flying Configurations
Author | : Adriana Nastase |
Publsiher | : Elsevier |
Total Pages | : 410 |
Release | : 2010-07-07 |
Genre | : Technology & Engineering |
ISBN | : 008055699X |
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Computation of Supersonic Flow over Flying Configurations is a high-level aerospace reference book that will be useful for undergraduate and graduate students of engineering, applied mathematics and physics. The author provides solutions for three-dimensional compressible Navier-Stokes layer subsonic and supersonic flows. Computational work and experimental results show the real-world application of computational results Easy computation and visualization of inviscid and viscous aerodynamic characteristics of flying configurations Includes a fully optimized and integrated design for a proposed supersonic transport aircraft
Supersonic Flow Computations for an ASTOVL Aircraft Configuration
Author | : Sekaripuram Ramakrishnan |
Publsiher | : Unknown |
Total Pages | : 48 |
Release | : 1990 |
Genre | : Aerodynamics, Supersonic |
ISBN | : NASA:31769000513765 |
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Supersonic Flow Computations for an Astovl Aircraft Configuration Phase 2
Author | : National Aeronautics and Space Administration (NASA) |
Publsiher | : Createspace Independent Publishing Platform |
Total Pages | : 46 |
Release | : 2018-07-12 |
Genre | : Electronic Book |
ISBN | : 1722829877 |
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A unified space/time marching method was used to solve the Euler and Reynolds-averaged Navier-Stokes equations for supersonic flow past an Advanced Short Take-off and Vertical Landing (ASTOVL) aircraft configuration. Lift and drag values obtained from the computations compare well with wind tunnel measurements. The entire calculation procedure is described starting from the geometry to final postprocessing for lift and drag. The intermediate steps include conversion from IGES to the patch specification needed for the CFD code, grid generation, and solution procedure. The calculations demonstrate the capability of the method used to accurately predict design parameters such as lift and drag for very complex aircraft configurations. Ramakrishnan, Sekaripuram V. and Chakravarthy, Sukumar R. and Szema, Kuo-Yen Unspecified Center NAS1-17492; RTOP 505-60-01-02...
Scientific and Technical Aerospace Reports
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 456 |
Release | : 1995 |
Genre | : Aeronautics |
ISBN | : UIUC:30112005546491 |
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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
High Angle of Attack Aerodynamics
Author | : Josef Rom |
Publsiher | : Springer Science & Business Media |
Total Pages | : 408 |
Release | : 2012-12-06 |
Genre | : Science |
ISBN | : 9781461228240 |
Download High Angle of Attack Aerodynamics Book in PDF, Epub and Kindle
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.
Difference Methods for Initial Boundary Value Problems and Flow Around Bodies
Author | : You-lan Zhu,Xi-chang Zhong,Bing-mu Chen,Zuo-min Zhang |
Publsiher | : Springer Science & Business Media |
Total Pages | : 606 |
Release | : 2013-06-29 |
Genre | : Mathematics |
ISBN | : 9783662067079 |
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Since the appearance of computers, numerical methods for discontinuous solutions of quasi-linear hyperbolic systems of partial differential equations have been among the most important research subjects in numerical analysis. The authors have developed a new difference method (named the singularity-separating method) for quasi-linear hyperbolic systems of partial differential equations. Its most important feature is that it possesses a high accuracy even for problems with singularities such as schocks, contact discontinuities, rarefaction waves and detonations. Besides the thorough description of the method itself, its mathematical foundation (stability-convergence theory of difference schemes for initial-boundary-value hyperbolic problems) and its application to supersonic flow around bodies are discussed. Further, the method of lines and its application to blunt body problems and conical flow problems are described in detail. This book should soon be an important working basis for both graduate students and researchers in the field of partial differential equations as well as in mathematical physics.
The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms
Author | : Max A. Heaslet |
Publsiher | : Unknown |
Total Pages | : 726 |
Release | : 1948 |
Genre | : Aerodynamics, Supersonic |
ISBN | : STANFORD:36105024795713 |
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A method is developed, consistent with the assumptions of small perturbation theory, which provides a means of determining for a known load distribution, the downwash behind a wing in supersonic flow. THe analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading.
Aeronautical Engineering
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 538 |
Release | : 1991 |
Genre | : Aeronautics |
ISBN | : UOM:39015023295143 |
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