Download or read book Calculation of Three dimensional Inviscid Supersonic Steady Flows written by Gino Moretti and published by . This book was released on 1982 with total page 162 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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.

Download or read book Calculation of the Three dimensional Supersonic Inviscid Steady Flow Past an Arrow winged Airframe written by Gino Moretti and published by . This book was released on 1976 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Analysis of Three dimensional Inviscid Supersonic Flow Between a Body and an Outer Wall written by W. C. Armstrong and published by . This book was released on 1976 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: The three-dimensional inviscid supersonic flow equations are solved for the flow over a body located within a duct. Numerical solutions are obtained by use of the reference plane method of characteristics technique. Results of the analysis are compared with experimental test body pressure distributions obtained with an off-design jet stretcher system. The analysis is sufficiently general so that a variety of internal flows may be predicted. A computer program listing and an example problem are presented.

Download or read book Calculation of Three Dimensional Supersonic Flow Fields about Aircraft Fuselages and Wings at General Angle of Attack written by Chong-Wei Chu and published by . This book was released on 1973 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new algorithm for the three-dimensional method of characteristics is applied to the calculation of steady inviscid supersonic flow about aircraft fuselages and wings at general angle of attack. After a brief discussion of the new method, computed results of flow over an elliptic cone and a blunt circular cone at angles of attack are presented and compared with available experimental data. Good agreement is observed. Application to fuselage flow field calculation then follows. Calculated examples of flow about typical fuselages under different flight conditions are presented, discussed, and compared with available experimental data with good agreement. Finally, the computed pressure distribution on a thin wing (an elliptic cone of 20:1 axis ratio) is presented and discussed. The present method can be used to obtain flow field information for aircraft design or to provide inviscid solutions for boundary layer analysis. (Author).

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 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 89 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.

Download or read book Three dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack written by G. Moretti and published by . This book was released on 1968 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Improved Supersonic Three dimensional External Inviscid Flow Field Code written by Frank Marconi and published by . This book was released on 1979 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Method of Characteristics for Steady Three dimensional Supersonic Flow with Application to Inclined Bodies of Revolution written by John V. Rakich and published by . This book was released on 1969 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: Characteristics method for determining three dimensional supersonic flow around inclined body of revolution.

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).

Download or read book A Supersonic Three Dimensional Code for Flow Over Blunt Bodies written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-25 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer code is described which may be used to calculate the steady, supersonic, three-dimensional, inviscid flow over blunt bodies. The theoretical and numerical formulation of the problem is given (shock-capturing, downstream marching), including exposition of the boundary and initial conditions. The overall flow logic of the program, its usage, accuracy, and limitations are discussed. Chaussee, D. S. and Mcmillan, O. J. Unspecified Center NASA-CR-3223, NEAR-TR-189 NAS1-15305

Download or read book Boundary Condition Computational Procedures for Inviscid Supersonic Steady Flow Field Calculations written by and published by . This book was released on 1971 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Complete Numerical Technique for the Calculation of Three dimensional Inviscid Supersonic Flows written by G. Moretti and published by . This book was released on 1972 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Calculation of Three Dimensional Supersonic Flows Around Spherically Capped Smooth Bodies and Wings Volume II Manual for Computer Programs written by Chong-Wei Chu and published by . This book was released on 1972 with total page 205 pages. Available in PDF, EPUB and Kindle. Book excerpt: I ;Powers, Sidney A. ;NOR-72-87-Vol-2F33615-72-C-1429AF-1366AFFDLTR-72-91-Vol-2See also Volume 1, AD-753 695.(*airframes, *supersonic characteristics), (*computer programs, aerodynamics), numerical analysis, conical bodies, delta wings, instruction manuals, blunt bodies, hypersonic characteristics, angle of attack, three dimensional flow, subroutinescomputer aided analysis, smooth bodies, inviscid flowThe report describes the theories, the numerical methods and the computer programs developed for determining the inviscid three-dimensional flow about smooth shapes at supersonic speeds. Volume II is a user's manual for the computer programs and provides the detailed information needed to set up and use the programs. These programs can determine the supersonic flow past smooth blunted bodies for any angle of attack for which the initial value surface remains on the blunted nose. The lowest usable Mach number is on the order of 2.0, with lower values attainable by careful attention to the initial value surface solution. There is no computational upper limit on the Mach number. (Author).

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:

Download or read book Solution of Some 3 D Viscous and Inviscid Supersonic Flow Problems by Finite Volume Space Marching Schemes written by H. Rieger and published by . This book was released on 1987 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: For prediction of steady supersonic flow fields two numerical methods for solution of the three-dimensional Euler-and parabolized Navier-Stokes (PNS- ) equations are considered. Both are based on a Finite-Volume discretisation (FVD) of the governing conservation laws and because of the special properties of steady supersonic flows cost-effective space-marching integration techniques can be applied. Both methods are described and results for inviscid and viscous flows are presented. In view of the upcoming European Space Transportation activities the simulation of hypersonic flows past complex blunted lifting vehicles requires also efficient methods for solution of the full, not-reduced Navier-Stokes equations. These are needed to provide solutions for super- and hypersonic flow fields with large subsonic regions and also to get accurate initial conditions for the space marching codes developed. A relaxation procedure for the steady form of the not-reduced Navier-Stokes and the Euler equations is described and some first results are presented.