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Computation Of Supersonic Flow Over Flying Configurations
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Book Synopsis Computation of Supersonic Flow over Flying Configurations by : Adriana Nastase
Download or read book Computation of Supersonic Flow over Flying Configurations written by Adriana Nastase and published by Elsevier. This book was released on 2010-07-07 with total page 425 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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
Book Synopsis Computation of Supersonic Flow over Flying Configurations by :
Download or read book Computation of Supersonic Flow over Flying Configurations written by and published by . This book was released on with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722829872 Total Pages :46 pages Book Rating :4.8/5 (298 download)
Book Synopsis Supersonic Flow Computations for an Astovl Aircraft Configuration, Phase 2 by : National Aeronautics and Space Administration (NASA)
Download or read book Supersonic Flow Computations for an Astovl Aircraft Configuration, Phase 2 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-12 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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...
Book Synopsis Supersonic Flow Computations Over Aerospace Configurations Using an Euler Marching Solver by :
Download or read book Supersonic Flow Computations Over Aerospace Configurations Using an Euler Marching Solver written by and published by . This book was released on 1987 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Flow Computations for an ASTOVL Aircraft Configuration by : Sekaripuram Ramakrishnan
Download or read book Supersonic Flow Computations for an ASTOVL Aircraft Configuration written by Sekaripuram Ramakrishnan and published by . This book was released on 1990 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis High Angle of Attack Aerodynamics by : Josef Rom
Download or read book High Angle of Attack Aerodynamics written by Josef Rom and published by Springer Science & Business Media. This book was released on 2012-12-06 with total page 408 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis The Calculation of Pressure on Slender Airplanes in Subsonic and Supersonic Flow by : Max A. Heaslet
Download or read book The Calculation of Pressure on Slender Airplanes in Subsonic and Supersonic Flow written by Max A. Heaslet and published by . This book was released on 1953 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt: Under the assumption that a wing, body, or wing-body combination is slender or flying at near sonic velocity, expressions are given which permit the calculation of pressure in the immediate vicinity of the configuration. The disturbance field, in both subsonic and supersonic flight, is shown to consist of two-dimensional disturbance fields extending laterally and a longitudinal field that depends on the streamwise growith of cross-sectional area. A discussioin is also given of couplings, between lifting and thickness effects, that necessarily arise as a result of the quadratic dependence of pressure on the induced velocity components.
Book Synopsis The Calculation of Three-dimensional Supersonic Flows Around Spherically-capped Smooth Bodies and Wings: Theory and applications by : Chong-Wei Chu
Download or read book The Calculation of Three-dimensional Supersonic Flows Around Spherically-capped Smooth Bodies and Wings: Theory and applications written by Chong-Wei Chu and published by . This book was released on 1972 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Calculation of Three-dimensional Supersonic Flows Around Spherically-capped Smooth Bodies and Wings: Manual for computer programs by : Chong-Wei Chu
Download or read book The Calculation of Three-dimensional Supersonic Flows Around Spherically-capped Smooth Bodies and Wings: Manual for computer programs written by Chong-Wei Chu and published by . This book was released on 1972 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of Supersonic Viscous Flow Over Delta Wings with Sharp Subsonic Leading Edges by : Y. C. Vigneron
Download or read book Calculation of Supersonic Viscous Flow Over Delta Wings with Sharp Subsonic Leading Edges written by Y. C. Vigneron and published by . This book was released on 1978 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations by : Jack Norman Nielsen
Download or read book Calculation of Laminar Separation with Free Interaction by the Method of Integral Relations written by Jack Norman Nielsen and published by . This book was released on 1966 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: "A calculative method is presented for determining separated, laminar, boundary-layer characteristics from in front of the separation point to the reattachment point under the influence of 'free interaction' between the main flow and the boundary layer. The analysis covers supersonic flow over two-dimensional and axisymmetric configurations with adiabatic or nonadiabatic wall conditions. For nonadiabatic wall conditions, theories based on first-order coupling and second-order coupling between velocity and total temperature profiles were presented. The theory based on first-order coupling was included in a machine calculation program with options for two-dimensional or axisymmetric flow and adiabatic or nonadiabatic wall conditions. Extensive systematic calculations were made to determine the range of possible separated flows over a two-dimensional configuration as a function of separation point location and wall temperatures. Comparison between experiment and theory for separation pressure distributions on two-dimensional or axisymmetric adiabatic configurations shows generally good agreement. Good comparison between experiment and theory is indicated for a moderately-cooled axisymmetric configuration. For a highly-cooled axisymmetric configuration, the prediction of the machine program based on first-order coupling is inadequate, indicating the necessity for a higher-order coupling theory." -- page iii.
Book Synopsis Thin-layer and Full Navier-Stokes Calculations for Turbulent Supersonic Flow Over a Cone at an Angle of Attack by : Crawford F. Smith
Download or read book Thin-layer and Full Navier-Stokes Calculations for Turbulent Supersonic Flow Over a Cone at an Angle of Attack written by Crawford F. Smith and published by . This book was released on 1993 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis External Flow Computations for a Finned 60MM Ramjet in Steady Supersonic Flight by : Bernard J. Guidos
Download or read book External Flow Computations for a Finned 60MM Ramjet in Steady Supersonic Flight written by Bernard J. Guidos and published by . This book was released on 1989 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The US Army Ballistic Research Laboratory (BRL) has participated in the development of the launch and flight technologies for a family of solid fuel ramjet (SFRU) projectiles. The ramjet is a tubular projectile which utilizes air ingested through the inlet to burn the solid fuel. When the combustion process ceases, the projectile becomes a high drag configuration. Several designs have been developed as potential tank gun training rounds (TGTR) for kinetic energy (KE) penetrators. This report documents a computational fluid dynamics study of the external aerodynamics of a finned 60mm solid-fuel ramjet in steady, supersonic, atmospheric flight. The main objective is to compute the external contribution to the pitch-plane aerodynamics using established in-house capabilities. Two space-marching finite-difference procedures are used to compute the external flow fields. Viscous flow results are generated using a thin-layer, parabolized Navier-Stokes technique; inviscid results are generated using an Euler solver. Results are shown for three configurations; Body-alone, body with original fins, and body with extended fins. The influence of initial marching conditions on the modeling of an inlet configuration is examined. A generalized scaling law is introduced which may improve the accuracy of future external space-marching flow computations for ramjets. Keywords: Fin-stabilized projectile; Supersonic flow; Wedge flow; Conical flow. (AW).
Book Synopsis Prediction of Unsteady Aerodynamic Loadings on Non-planar Wings and Wing-tail Configurations in Supersonic Flow by : Jack Morito (II)
Download or read book Prediction of Unsteady Aerodynamic Loadings on Non-planar Wings and Wing-tail Configurations in Supersonic Flow written by Jack Morito (II) and published by . This book was released on 1972 with total page 438 pages. Available in PDF, EPUB and Kindle. Book excerpt: A three-dimensional extension of the Mach Box technique was developed for the unsteady aerodynamic analysis of non-planar wings and wing-tail configurations in supersonic flow. Various refinement procedures were included to improve the accuracy of the results. A general purpose computer program was written for the CDC 6600. The program is capable of treating wing-tail combinations with or without vertical separation, longitudinal separation and dihedral on either surface. If a wing alone is treated, perturbation velocity components in the flow field may be found. Correlations with experimental flutter results were performed for several models tested in the low supersonic Mach number range. The methods are intended to be used by airplane designers to calculate with improved accuracy, the unsteady aerodynamic loads that act on a lifting surface being propelled at supersonic speeds. The new feature of these calculations is that the aerodynamic interference between the wing and tail was taken into account. These calculations are an essential ingredient of flutter analyses and will improve the confidence level of such calculations in preventing wing-tail flutter.
Book Synopsis Commercial Supersonic Technology by : National Research Council
Download or read book Commercial Supersonic Technology written by National Research Council and published by National Academies Press. This book was released on 2002-02-16 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: High-speed flight is a major technological challenge for both commercial and business aviation. As a first step in revitalizing efforts by the National Aeronautics and Space Administration (NASA) to achieve the technology objective of high-speed air travel, NASA requested the National Research Council (NRC) to conduct a study that would identify approaches for achieving breakthroughs in research and technology for commercial supersonic aircraft. Commercial Supersonic Technology documents the results of that effort. This report describes technical areas where ongoing work should be continued and new focused research initiated to enable operational deployment of an environmentally acceptable, economically viable commercial aircraft capable of sustained supersonic flight, including flight over land, at speeds up to approximately Mach 2 in the next 25 years or less.
Book Synopsis Numerical Computations of Supersonic Base Flow with Special Emphasis on Turbulence Modeling by :
Download or read book Numerical Computations of Supersonic Base Flow with Special Emphasis on Turbulence Modeling written by and published by . This book was released on 1994 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A zonal, implicit, time-marching Navier-Stokes computational technique has been used to compute the turbulent supersonic base flow over cylindrical afterbodies. A critical element of calculating such flows is the turbulence model. Various eddy viscosity turbulence models have been used in the base region flow computations. These models include two algebraic turbulence models and a two-equation k-epsilon model. The k-epsilon equations are developed in a general coordinate system and solved using an implicit algorithm. Calculations with the k-epsilon model are extended up to the wall. Flow field computations have been performed for a cylindrical afterbody at M = 2.46 and at angle of attack alpha = 0. The results are compared to the experimental data for the same conditions and the same configuration. Details of the mean flow field as well as the turbulence quantifies have been presented. In addition, the computed base pressure distribution has been compared with the experiment. In general, the k-epsilon turbulence model performs better in the near wake than the algebraic models and predicts the base pressure much better. Base flow, Base pressure, Turbulence models, Wake, Supersonic flow.
Book Synopsis Computation of Multi-dimensional Viscous Supersonic Flow by : R. C. Buggeln
Download or read book Computation of Multi-dimensional Viscous Supersonic Flow written by R. C. Buggeln and published by . This book was released on 1986 with total page 202 pages. Available in PDF, EPUB and Kindle. Book excerpt:
