Computation of Three-dimensional Nozzle-exhaust Flow Fields with the GIM Code
Author : L. W. Spradley
Publisher :
Page : 84 pages
File Size : 18,77 MB
Release : 1978
Category : Aerodynamics
ISBN :
Author : L. W. Spradley
Publisher :
Page : 84 pages
File Size : 18,77 MB
Release : 1978
Category : Aerodynamics
ISBN :
Author : L. W. Spradley
Publisher :
Page : 84 pages
File Size : 26,67 MB
Release : 1978
Category : Aerodynamics
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Author :
Publisher :
Page : 268 pages
File Size : 27,82 MB
Release : 1978
Category : Aeronautics
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Author :
Publisher :
Page : 104 pages
File Size : 27,72 MB
Release : 1980
Category : Aeronautics
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Author : L. W. Spradley
Publisher :
Page : 188 pages
File Size : 14,31 MB
Release : 1980
Category : Boundary layer
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low fields in supersonic inlet configurations were computed using the eliptic GIM code on the STAR computer. Spillage flow under the lower cowl was calculated to be 33% of the incoming stream. The shock/boundary layer interaction on the upper propulsive surface was computed including separation. All shocks produced by the flow system were captured. Linearized block implicit (LBI) schemes were examined to determine their application to the GIM code. Pure explicit methods have stability limitations and fully implicit schemes are inherently inefficient; however, LBI schemes show promise as an effective compromise. A quasiparabolic version of the GIM code was developed using elastical parabolized Navier-Stokes methods combined with quasitime relaxation. This scheme is referred to as quasiparabolic although it applies equally well to hyperbolic supersonic inviscid flows. Second order windward differences are used in the marching coordinate and either explicit or linear block implicit time relaxation can be incorporated. (NTRL site)
Author : V. H. Ransom
Publisher :
Page : 10 pages
File Size : 14,81 MB
Release : 1969
Category : Airplanes
ISBN :
In this paper a new second-order numerical method of characteristics for calculation of three-dimensional steady supersonic flow is described. The method has been programmed for the CDC 6500 and IBM 7094 computers. Numerical results have been obtained which verify the second order numerical accuracy and the numerical stability of the scheme. In addition, computed results for an axisymmetric nozzle are compared with the solution obtained using a two independent variable method of characteristics program and the two results are found to be in good agreement. The numerical solution for the flow in a representative three-dimensional nozzle is presented. (Author).
Author :
Publisher :
Page : 840 pages
File Size : 43,54 MB
Release : 1979
Category : Mechanics, Applied
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Author :
Publisher :
Page : 196 pages
File Size : 11,41 MB
Release : 1988
Category :
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Author :
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Page : 1136 pages
File Size : 12,94 MB
Release : 1979
Category : Government publications
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Author : United States. Superintendent of Documents
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Page : 1122 pages
File Size : 19,43 MB
Release : 1968
Category : Government publications
ISBN :