Download or read book An Improved Supersonic Three Dimensional External Inviscid Flow Field Code 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 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A numerical procedure was developed to compute the inviscid super/hypersonic flow fields about complex vehicle geometries accurately and efficiently. A second-order accurate finite difference scheme is used to integrate the three-dimensional Euler equations in regions of continuous flow, while all shock waves are computed as discontinuities via the Rankine-Hugoniot jump conditions. Conformal mappings are used to develop a computational grid. The effects for equilibrium air are included using curve fits of Mollier charts. This report deals only with modifications to these procedures in four specific areas: inlet mass ingestion, subsonic axial Mach number, improved conformal mappings, and vehicles flying at yaw. In each area both the modifications to the computational procedures and computer code are discussed. Marconi, F. and Koch, F. Unspecified Center NASA-CR-3108 NAS1-14162; RTOP 505-11-31-02

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 36 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 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 236 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 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 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 Three dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack written by M. J. Abbett and published by . This book was released on 1968 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt: The solution for the steady three-dimensional inviscid flow about supersonic blunt cones at angle of attack is obtained by coupling a direct time-dependent solution for the subsonic portion of the shock layer with steady state numerical afterbody solution. An outline is given covering the coupling scheme and the use of the resulting Fortran computer code.

Download or read book NASA Technical Paper written by and published by . This book was released on 1990 with total page 748 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 836 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 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 NASA Technical Memorandum written by and published by . This book was released on 1982 with total page 310 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 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 Applied Mechanics Reviews written by and published by . This book was released on 1980 with total page 932 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Theoretical and Experimental Flow Fields for a Supersonic Cruise Fighter Forebody written by Steven F. Yaros and published by . This book was released on 1985 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Theoretical and Experimental Engine inlet Flow Fields for Fighter Forebodies written by Steven F. Yaros and published by . This book was released on 1984 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Monthly Catalog of United States Government Publications written by United States. Superintendent of Documents and published by . This book was released on 1979 with total page 1250 pages. Available in PDF, EPUB and Kindle. Book excerpt: February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index

Download or read book Monthly Catalogue United States Public Documents written by and published by . This book was released on 1979 with total page 1256 pages. Available in PDF, EPUB and Kindle. Book excerpt: