The Calculation of Three-dimensional Supersonic Flows Around Spherically-capped Smooth Bodies and Wings: Manual for computer programs PDF Download
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Author: Chong-Wei Chu
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 216
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Book Description
Author: Chong-Wei Chu
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 216
Get Book Here
Book Description
Author: Chong-Wei Chu
Publisher:
ISBN:
Category :
Languages : en
Pages : 205
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Book Description
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).
Author: Chong-Wei Chu
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 92
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 89
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Book Description
The 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 1 describes the theoretical and numerical approaches and compares two sample cases with experiment; a blunted 15 deg cone at 20 deg angle of attack in helium at M = 14. 9, and a 70 deg slab delta wing at 15 deg angle of attack in air at M = 9.6. The numerical results are in close agreement with the experimental data.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1102
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 890
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 616
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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:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1080
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Author:
Publisher:
ISBN:
Category : Technology
Languages : en
Pages : 1204
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