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An Inviscid Computational Method For Supersonic Inlets
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Book Synopsis An Inviscid Computational Method for Supersonic Inlets by :
Download or read book An Inviscid Computational Method for Supersonic Inlets written by and published by . This book was released on 1984 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An extension to the SWINT code is described which permits inviscid calculations to be performed on the supersonic portion of inlet flow fields. Also described is an interface program which rezones the external flow field applied to several examples. A listing of the extension to SWINT and the interface program are provided in the Appendices along with a set of user instructions and a sample case. (Author).
Book Synopsis An Inviscid Computational Method for Supersonic Inlets by : A. B Wardlaw (Jr)
Download or read book An Inviscid Computational Method for Supersonic Inlets written by A. B Wardlaw (Jr) and published by . This book was released on 1984 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: An extension to the SWINT code is described which permits inviscid calculations to be performed on the supersonic portion of inlet flow fields. Also described is an interface program which rezones the external flow field applied to several examples. A listing of the extension to SWINT and the interface program are provided in the Appendices along with a set of user instructions and a sample case. (Author).
Book Synopsis A Program for Computing Steady Inviscid Three-dimensional Supersonic Flow on Reentry Vehicles by : J. M. Solomon
Download or read book A Program for Computing Steady Inviscid Three-dimensional Supersonic Flow on Reentry Vehicles written by J. M. Solomon and published by . This book was released on 1977 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive computational procedure is presented for predicting the supersonic region of the flow field on advanced reentry vehicle shapes in steady flight at pitch and yaw. The procedure utilizes explicit second order accurate finite difference methods applied to the conservation law form of the steady inviscid flow equations. Improved numerical methods are used at the body surface and the bow shock wave. Provisions for treating body geometries with discontinuous slopes are also included. Either perfect gas or real gas equilibrium thermodynamic properties can be used. The computational procedure is implemented as a fortran computer code which provides a practicable representation of the inviscid flow field and the resulting aerodynamic force and moment on the vehicle. This volume contains detailed instructions for operating the code and interpreting the output results.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781719390408 Total Pages :26 pages Book Rating :4.3/5 (94 download)
Book Synopsis Design and Analysis Tool for External-Compression Supersonic Inlets by : National Aeronautics and Space Administration (NASA)
Download or read book Design and Analysis Tool for External-Compression Supersonic Inlets written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-22 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational tool named SUPIN has been developed to design and analyze external-compression supersonic inlets for aircraft at cruise speeds from Mach 1.6 to 2.0. The inlet types available include the axisymmetric outward-turning, two-dimensional single-duct, two-dimensional bifurcated-duct, and streamline-traced Busemann inlets. The aerodynamic performance is characterized by the flow rates, total pressure recovery, and drag. The inlet flowfield is divided into parts to provide a framework for the geometry and aerodynamic modeling and the parts are defined in terms of geometric factors. The low-fidelity aerodynamic analysis and design methods are based on analytic, empirical, and numerical methods which provide for quick analysis. SUPIN provides inlet geometry in the form of coordinates and surface grids useable by grid generation methods for higher-fidelity computational fluid dynamics (CFD) analysis. SUPIN is demonstrated through a series of design studies and CFD analyses were performed to verify some of the analysis results. Slater, John W. Glenn Research Center COMPUTATIONAL FLUID DYNAMICS; SUPERSONIC INLETS; FLOW DISTRIBUTION; AERODYNAMIC CHARACTERISTICS; DRAG; FLOW VELOCITY; SUPERSONIC SPEED; DUCTS; PRESSURE RECOVERY; DESIGN ANALYSIS
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722136253 Total Pages :64 pages Book Rating :4.1/5 (362 download)
Book Synopsis A Method for Generating Reduced Order Linear Models of Supersonic Inlets by : National Aeronautics and Space Administration (NASA)
Download or read book A Method for Generating Reduced Order Linear Models of Supersonic Inlets written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-02 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: For the modeling of high speed propulsion systems, there are at least two major categories of models. One is based on computational fluid dynamics (CFD), and the other is based on design and analysis of control systems. CFD is accurate and gives a complete view of the internal flow field, but it typically has many states and runs much slower dm real-time. Models based on control design typically run near real-time but do not always capture the fundamental dynamics. To provide improved control models, methods are needed that are based on CFD techniques but yield models that are small enough for control analysis and design. Chicatelli, Amy and Hartley, Tom T. Glenn Research Center...
Book Synopsis A Method for Generating Reduced Order Linear Models of Supersonic Inlets by : National Aeronautics and Space Adm Nasa
Download or read book A Method for Generating Reduced Order Linear Models of Supersonic Inlets written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2020-04-08 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: For the modeling of high speed propulsion systems, there are at least two major categories of models. One is based on computational fluid dynamics (CFD), and the other is based on design and analysis of control systems. CFD is accurate and gives a complete view of the internal flow field, but it typically has many states and runs much slower dm real-time. Models based on control design typically run near real-time but do not always capture the fundamental dynamics. To provide improved control models, methods are needed that are based on CFD techniques but yield models that are small enough for control analysis and design. Chicatelli, Amy and Hartley, Tom T. Glenn Research Center...
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Inlet Flow Computations Using Fortified Navier-Stokes Approach by : Shinichi Kuroda
Download or read book Supersonic Inlet Flow Computations Using Fortified Navier-Stokes Approach written by Shinichi Kuroda and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Design of Supersonic Inlets by a Computer Program Incorporating the Method of Characteristics by : Bernhard H. Anderson
Download or read book Design of Supersonic Inlets by a Computer Program Incorporating the Method of Characteristics written by Bernhard H. Anderson and published by . This book was released on 1969 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Technique for Computing Three-dimensional Steady Inviscid Supersonic Flows by : GINO. MORETTI
Download or read book A Technique for Computing Three-dimensional Steady Inviscid Supersonic Flows written by GINO. MORETTI and published by . This book was released on 1960 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: A thorough understanding of the supersonic flow past an arbitrarily shaped body can only be achieved by solving the three-dimensional aerodynamic problem. It is well known that only numerical techniques can be used, because of the nonlinearity of the equations. Nevertheless, in the field of engineering, a quick, panoramic survey of a problem is often much more interesting and useful than the exact solution on one particular case. With this in mind, we attempted the building up of a technique to be used on a small computing machine. Its advantages are: the simplicity of the program, which can be understood and eventually modified by engineers, not specially skilled in programming; a direct control of the results, as far as they are typed out; the choice of different degrees of approximation, including a very rough one, apt for getting a first insight on a given body under several conditions, and seeing how it works. In this report, the essential features of the problem are first examined to obtain suggestions for setting up a technique, and then the numerical procedure which has been set up and programmed is outlined.
Download or read book NASA SP. written by and published by . This book was released on 1990 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Computation of Internal and External Flows, Volume 2 by : Charles Hirsch
Download or read book Numerical Computation of Internal and External Flows, Volume 2 written by Charles Hirsch and published by Wiley. This book was released on 1991-01-08 with total page 724 pages. Available in PDF, EPUB and Kindle. Book excerpt: Numerical Computation of Internal and External Flows Volume 2: Computational Methods for Inviscid and Viscous Flows C. Hirsch, Vrije Universiteit Brussel, Brussels, Belgium This second volume deals with the applications of computational methods to the problems of fluid dynamics. It complements the first volume to provide an excellent reference source in this vital and fast growing area. The author includes material on the numerical computation of potential flows and on the most up-to-date methods for Euler and Navier-Stokes equations. The coverage is comprehensive and includes detailed discussion of numerical techniques and algorithms, including implementation topics such as boundary conditions. Problems are given at the end of each chapter and there are comprehensive reference lists. Of increasing interest, the subject has powerful implications in such crucial fields as aeronautics and industrial fluid dynamics. Striking a balance between theory and application, the combined volumes will be useful for an increasing number of courses, as well as to practitioners and researchers in computational fluid dynamics. Contents Preface Nomenclature Part V: The Numerical Computation of Potential Flows Chapter 13 The Mathematical Formulations of the Potential Flow Model Chapter 14 The Discretization of the Subsonic Potential Equation Chapter 15 The Computation of Stationary Transonic Potential Flows Part VI: The Numerical Solution of the System of Euler Equations Chapter 16 The Mathematical Formulation of the System of Euler Equations Chapter 17 The Lax - Wendroff Family of Space-centred Schemes Chapter 18 The Central Schemes with Independent Time Integration Chapter 19 The Treatment of Boundary Conditions Chapter 20 Upwind Schemes for the Euler Equations Chapter 21 Second-order Upwind and High-resolution Schemes Part VII: The Numerical Solution of the Navier-Stokes Equations Chapter 22 The Properties of the System of Navier-Stokes Equations Chapter 23 Discretization Methods for the Navier-Stokes Equations Index
Book Synopsis Calculation of Two-dimensional Inlet Flow Fields by an Implicit Method Including Viscous Effects by : Sedat Biringen
Download or read book Calculation of Two-dimensional Inlet Flow Fields by an Implicit Method Including Viscous Effects written by Sedat Biringen and published by . This book was released on 1981 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Inlet flow fields for airbreathing missiles are calculated by the adaptation of a two dimensional computational method developed for the flow around airfoils. A supersonic free stream is assumed to allow the forebody calculation to be uncoupled from the inlet calculation. The inlet calculation employs an implicit, time marching finite difference procedure to solve the thin layer Navier-Stokes equations formulated in body fitted coordinates. The mathematical formulation of the problem and the solution algorithm are given. Numerical stability and accuracy as well as the initial and boundary conditions used are discussed. Instructions for program use and operation along with the overall program logic are also given.
Book Synopsis A Multiple Zone Method for Supersonic Tactical Missiles by :
Download or read book A Multiple Zone Method for Supersonic Tactical Missiles written by and published by . This book was released on 1986 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A practical means of predicting the inviscid flow field about a supersonic missile is to numerically solve the steady, three-dimensional Euler equations. A major problem encountered in steady, supersonic calculations is the treatment of complex cross-sectional geometries which arise in conjunction with configurations featuring fins, inlets and tails. An alternative approach for treating complex missile and aircraft configurations is a multiple zone strategy. A multiple zone computational method applicable to finned bodies is supersonic flight is described. At each cross-section, the computational domain is broken into a number of zones, each of which can be described using a simple mapping. The zones are chosen to ensure that the bow shock, fin and body surfaces coincide with zone edges. At zone interfaces, the mesh may be discontinuous in a direction normal to the edge. Along zone edges, surfaces are allowed to form or disappear during the computation. The surface edges which form at points where surfaces appear or disappear are treated using a local analysis. The resulting algorithm is applicable to a wide range of configurations including interior as well as exterior supersonic flow fields. Calculations are compared to experiment for several different missile shapes. Keywords: Numerical methods.
Book Synopsis A Program for Computing Steady Inviscid Three-dimensional Supersonic Flow on Reentry Vehicles by : J. M. Solomon
Download or read book A Program for Computing Steady Inviscid Three-dimensional Supersonic Flow on Reentry Vehicles written by J. M. Solomon and published by . This book was released on 1977 with total page 229 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive computational procedure is presented for predicting the supersonic region of the flow field on advanced reentry vehicle shapes in steady flight at pitch and yaw. The procedure utilizes explicit second order accurate finite difference methods applied to the conservation law form of the steady inviscid flow equations. Improved numerical methods are used at the body surface and the bow shock wave. Provisions for treating body geometries with discontinuous slopes are also included. Either perfect gas or real gas equilibrium thermodynamic properties can be used. The computational procedure is implemented as a FORTRAN computer code which provides a practicable representation of the inviscid flow field and the resulting aerodynamic force and moment on the vehicle. In this report (Vol. I) the analytical and numerical development of the procedure is presented and the associated computer code is described. A comparison report (Vol. II User's Manual) contains detailed instructions for operating the code and interpreting the output results. (Author).
Book Synopsis Large Eddy Simulation of Supersonic Inlet Flows by :
Download or read book Large Eddy Simulation of Supersonic Inlet Flows written by and published by . This book was released on 1998 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The interaction of a shock wave with a turbulent boundary layer is a central problem in supersonic inlet flows. This work uses numerical and analytical techniques to study shock/turbulence interaction in order to identify and explain factors important in shock/boundary layer interaction. Direct numerical simulation of a normal shock wave with an isotropic turbulent field of vorticity and entropy fluctuations showed that negative upstream correlation between the vorticity and entropy fluctuations enhances the turbulence across the shock. Positive upstream correlation has a suppressing effect. A new numerical method providing excellent high wavenumber resolution while reducing the computational cost was developed. A model with no adjustable constants was developed to study the vortex breakdown resulting from the interaction of canard or forbody vortices with the shock waves in a supersonic inlet flow. Very good agreement with both experiment and computation was obtained. A numerical method to compute shock/turbulence interaction using a conservative form of the Large Eddy Simulation (LES) equations has been developed and validated. LES of the interaction of isotropic turbulence with a normal shock was performed and comparisons with direct numerical simulation (DNS) results were favorable. A new Fortran 90 code has been developed for the computation of shock/turbulence interaction. The code is an improved version of codes used previously in shock/turbulence interaction simulations.
Book Synopsis Development of a Three-dimensional Supersonic Inlet Flow Analysis by :
Download or read book Development of a Three-dimensional Supersonic Inlet Flow Analysis written by and published by . This book was released on 1980 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
