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 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 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 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 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 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 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 Scientific and Technical Aerospace Reports written by and published by . This book was released on with total page 994 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book STAR written by and published by . This book was released on 1973 with total page 920 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1977 with total page 1166 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Numerical Grid Generation Techniques written by and published by . This book was released on 1980 with total page 598 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Workshop on Numerical Grid Generation Techniques for Partial Differential Equations October 6 7 1980 written by and published by . This book was released on 1980 with total page 306 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Prediction of the Pressure Fluctuations Associated with Maneuvering Reentry Weapons written by Anthony L. Laganelli and published by . This book was released on 1984 with total page 184 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was conducted at the AEDC von Karman facility, Tunnels A and B, in which acoustic pressure fluctuation data were acquired on a 7 degree half-cone-angle model featuring a control surface. The objective was to define the aeroacoustic environment applicable to re-entry vibration response analysis for both ballistic and maneuvering vehicles. Wind tunnel measurements were obtained at Mach 4 and 8 for several values of freestream Reynolds number and model angle of attack. Stationary zones of laminar, transitional, and turbulent flow over the model were achieved. Acoustic data were reduced to rms fluctuating pressure, and power and cross-power spectral densities. Results were normalized using local boundary layer parameters for comparison with previous high speed measurements. The present study re-examined the aeroacoustic environment prediction capability relative to compressible flow conditions. Moreover, boundary layer characteristic lengths and velocities were reviewed in order to develop normalization procedures required for development of appropriate aeroacoustic scaling laws. It was determined that fluctuating pressure characteristics described by incompressible theory as well as empirical correlations could be modified to a compressible state through a transformation function. In this manner, compressible data were transformed to the incompressible plane where direct use of more tractable prediction techniques are available for engineering design analyses.

Download or read book AIAA 86 0200 AIAA 86 0250 written by and published by . This book was released on 1986 with total page 476 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Computer Program for Three Dimensional Supersonic Flow with Arbitrarily Defined Boundaries written by Brian A. McIntyre and published by . This book was released on 1972 with total page 182 pages. Available in PDF, EPUB and Kindle. Book excerpt: A production type computer program has been developed, for the CDC-6500 computer, which is capable of solving supersonic flow problems through arbitrarily shaped three-dimensional geometries. Provisions have been made for the inclusion of an arbitrarily shaped three-dimensional centerbody in the flow. The geometry of the contours may be specified by tabular data or by expressing parameters in an analytic equation. A second-order numerical method of characteristics is used to solve the equations of motion for three-dimensional, steady supersonic flow. (Author).

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: