A class of nonlinear functions and the convergence of Gauss-Seidel and Newton-Gauss-Seidel iterations
Class on nonlinear functions and convergence of Gauss-Seidel and Newton-Gauss-Seidel iterations
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Class on nonlinear functions and convergence of Gauss-Seidel and Newton-Gauss-Seidel iterations
Error analysis for extraterrestrial convergent photogrammetric mapping system
Convergence of centers algorithm for solving nonlinear programming problems
NASTRAN flat plate finite element convergence properties for stress analysis of cylindrical and conical shells
Partial differential equations finite difference approximation, applying convergence theorems with probabilistic method
Weighted least squares nonlinear estimation problem, presenting partial step algorithm for convergence region enlargement
Convergence rates of multistep iterative procedures for finding zero of nonlinear function defined on R to nth power
Convergence of identification scheme for scalar- input-scalar-output linear systems with random inputs, applying invariant set theorem for random systems
Rapidly converging first order training algorithm for adaptive equalizer design in PAM signal reception, using variable step sizes for mean- square error minimization
Orders of convergence for iterative procedures for finding zero of nonlinear function, considering secant and Steffenson method
Global convergence of iterative schemes by Newton-Gauss-Seidel method, considering discrete approximations of elliptic partial differential equations
Turbulent boundary layer and heat transfer measurements along cooled conical convergent- divergent nozzle
Rapidly converging second order optimal tracking algorithms for adaptive equalization on basis of estimated bounds for eigenvalues of signal plus noise correlation matrix
Underthrusting mechanism during southwest Japan earthquakes, presenting model of convergent plate interactions
The theory of consistent step-by-step methods for solving Volterra integral equations is extended to nonsingular Volterra integro-differential equations. It is shown that standard step-by-step algorithms for these more general equations are convergent. Several numerical examples are included.
An analytical solution for the compressible one-dimensional flow in convergent and divergent ducts with friction is obtained. It is found that a nondimensional parameter, N, can be formed using the friction factor, duct half-angle and the ratio of specific heats of the gas. Seven flow regimes are describable with the solution, based on certain bounds on the magnitude of N. The regimes are discussed and corollary data are presented graphically.
The problem of the transmission of sound in a duct with very thin shear layers at the walls is treated by an inner expansion method. The results show that the formulation of the problem of the transmission of sound in a duct with a shear layer at the wall converges, in the case of a vanishingly thin shear layer, to the formulation of the same problem when uniform flow is assumed and the wall boundary condition is that of continuity of particle displacement.
Twin-jet afterbody models were investigated by using two balances to measure the thrust-minus-total drag and the afterbody drag, separately, at static conditions and at Mach numbers up to 2.2 for an angle of attack of 0 deg. Hinged-flap convergent-divergent nozzles were tested at subsonic-cruise- and maximum-afterburning-power settings with a high-pressure air system used to provide jet-total-pressure ratios up to 20. Two nozzle lateral spacings were studied, using afterbodies with similar interfairing shapes but with different longitudinal cross-sectional area distributions. Alternate, blunter, interfairings with different shapes for the two spacings, which produced afterbodies having identical cross-sectional area progressions corresponding to an axisymmetric minimum wave-drag configuration, were also tested. The results indicate that the wide-spaced configurations improved the flow field around the nozzles, thereby reducing drag on the cruise nozzles; however, the increased surface and projected cross-sectional areas caused an increase in afterbody drag. Except for a slight advantage with cruise nozzles at subsonic speeds, the wide-spaced configurations had the higher total drag at all other test conditions.