Three-dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack PDF Download
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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: 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: G. Moretti
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
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Book Description
Comparisons are made between the cylindrical and polar coordinate system used in determining the three-dimensional shock layer flow over the nose region of a blunted supersonic vehicle. Jusfification for the development of a polar coordinate system is given and an outline for such development is presented. Results from the polar coordinate system are given as is the limiting useful range.
Author: G. Moretti
Publisher:
ISBN:
Category :
Languages : en
Pages : 80
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Book Description
Author: General Applied Science Laboratories (Westbury, Nassau County, N.Y.)
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 130
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
The three-dimensional flow field around blunted bodies traveling at supersonic speed is computed using a time-dependent technique. The problem is mathematically well posed, the technique is stable and its accuracy increases with the fineness of the mesh. Values at points within the shock layer are computed by a method closely related to the Lax-Wendroff technique. Values at shock points and body points are computed by a four-dimensional method of characteristics.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
The three-dimensional ideal gas flow in the shock layer of a blunted supersonic cone at an angle of attack is calculated using two asymptotic solutions. The first solution calculates the steady state flow in the subsonic nose region by obtaining a time-dependent solution of the hyperbolic equations using numerical techniques. Internal, nonboundary points are calculated using a Lax-Wendroff numerical type technique. Boundary points, shock and body surface, are computed using a time-dependent method of characteristics. When a steady state solution is reached the flow properties on a surface of constant [theta], (where the Mach number is everywhere> 1) are used for initial data for the afterbody solution. The afterbody solution, using polar coordinates (r, [theta], [phi]) assumes at r0 an arbitrary set of initial conditions provided by the nose region solution and computes the downstream flow as a function of [theta], [phi], and r until an asymptotic state independent of r develops. The interior mesh points are again calculated using a Lax- Wendroff type technique and the boundary points by a method of characteristics. This report covers the coupling of the time-dependent and radius (r) dependent solutions. Instructions are given for the operation of the resulting Fortran code. The type of input data required is detailed and sample output is provided. Output data is given in two sets of coordinates. One is wind orientated; the other set is given in body orientated coordinates; The analytical transformation from one coordinate system to the other is given.
Author: D. S. Chaussee
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 32
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Book Description
Author: George F. Widhopf
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 56
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Book Description
A simple correlation of the local nondimensional heat transfer rate with the local nondimensional pressure ratio for blunt cones at angles of attack is presented. The correlation is demonstrated utilizing two comprehensive sets of experimental data; one for the turbulent case and one for the laminar case. In each case, the correlation is of the form of a set of power laws (an individual power law for each conical surface location) and includes the effect of streamline spreading and entropy swallowing on the evaluation of the local heat transfer rate. At each station, the individual power law correlates the circumferential variation for a spectrum of angles of attack. It is shown that the slope of each of the individual power laws in a particular set is the same and that the power law coefficient can be accurately predicted from the zero angle-of-attack distribution. Numerical and analytic results are presented which identify the dependence of the nondimensional heat transfer rates on the various independent flow parameters and also indicate the extension of this type of correlation to conditions other than the experimental ones considered herein. (Author).
Author: Dale Anderson
Publisher: Taylor & Francis
ISBN: 1466578300
Category : Science
Languages : en
Pages : 763
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Book Description
Thoroughly updated to include the latest developments in the field, this classic text on finite-difference and finite-volume computational methods maintains the fundamental concepts covered in the first edition. As an introductory text for advanced undergraduates and first-year graduate students, Computational Fluid Mechanics and Heat Transfer, Thi
Author: Roie R. Balck
Publisher:
ISBN:
Category :
Languages : en
Pages : 145
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Book Description
A system of six computer programs which may be arranged into several program packages for the purpose of solving inviscid flow fields over sharp and spherically blunted cones at angle of attack in both uniform and nonuniform supersonic free streams has been developed. These programs are written in standard FORTRAN 4 and are currently being run on the Virginia Polytechnic Inst. and State University IBM 370/155 computer. The six programs include a modified inverse blunt body solution program, a modified axisymmetric method of characteristics program, a modified three-dimensional method of characteristics program, two sharp cone zero and nonzero angle of attack uniform flow solution programs, and a master data input control program which reads input data and passes information to the other programs. (Modified author abstract).
