A Program for Computing Steady Inviscid Three-dimensional Supersonic Flow on Reentry Vehicles PDF Download
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Author: J. M. Solomon
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 236
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Book Description
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).
Author: J. M. Solomon
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 236
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Book Description
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).
Author: J. M. Solomon
Publisher:
ISBN:
Category : Boundary value problems
Languages : en
Pages : 106
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Book Description
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: J. M. Solomon
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 229
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Book Description
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).
Author: J. M. Solomon
Publisher:
ISBN:
Category : Boundary value problems
Languages : en
Pages : 89
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Book Description
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: GINO. MORETTI
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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Book Description
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.
Author: Frank Marconi
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
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Book Description
Author: M. J. Abbett
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 126
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Book Description
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.
Author: W. C. Armstrong
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 98
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Book Description
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.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1572
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Book Description
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1166
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Book Description
