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
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
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
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: George F. Widhopf Publisher: ISBN: Category : Heat Languages : en Pages : 56
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
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: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 580
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Author: M. J. Abbett
Author: M. J. Abbett
Author: G. Moretti
Author: G. Moretti
Author: General Applied Science Laboratories (Westbury, Nassau County, N.Y.)
Author: G. Moretti
Author: George F. Widhopf
Author: Dale Anderson
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Author: 
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