Base flow field investigation on the S-2 stage
Modified computer program using finite difference method for calculating base flow field and dissipation for Saturn S-2 stage
Dattorre, L.↗
SEARCH · Search NASA
Results for “finite difference method”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Teddy - A two-dimensional Lagrangian code for determining the wave propagation in elastic-plastic media
Finite difference methods and two dimensional Lagrangian code for determining wave propagation in elastic-plastic media - TEDDY program
Jones, A. H.↗
A study of the transient flow field ahead of a sphere which has been struck by a normal shock wave
Finite difference method of solving normal shock wave-sphere interaction problem for ideal and real gas flow fields
Barnell, R. W.↗
Programs for computation of velocities and stream-lines on a blade-to-blade surface of a turbomachine.
Finite difference method computer programs for calculation of velocities and streamlines on blade to blade surface of revolution of turbomachine
Katsanis, T.↗
Calculation of nonequilibrium hypersonic turbulent boundary layers and comparisons with experimental data.
Compressible hypersonic turbulent boundary layers solution by finite difference method, relating mixing length to velocity profile shape factor
Beckwith, I. E.↗
Numerical integration of products of Fourier and ordinary polynomials
Coefficients for finite difference methods of numerical integration of products of Fourier and ordinary polynomials
Bettis, D. G.↗
Calculation of nonequilibrium hypersonic turbulent boundary layers and comparisons with experimental data
Compressible hypersonic turbulent boundary layers solution by finite difference method, relating mixing length to velocity profile shape factor
Beckwith, I. E.↗
Stress, buckling, and vibration analysis of shells of revolution
Stress, buckling and vibration analysis of shells of revolution by numerical integration and finite difference methods, summarizing computer programs
Anderson, M. S.↗
Computer program calculates transonic velocities in turbomachines
Computer program, TSONIC, combines velocity gradient and finite difference methods to obtain numerical solution for ideal, transonic, compressible flow for axial, radial, or mixed flow cascade of turbomachinery blades.
Katsanis, T.↗
The compressible turbulent boundary layer on a blunt swept slab with and without leading- edge blowing
Finite difference method for solving equations for compressible turbulent boundary layers on swept infinite cylinders
Beckwith, I. E.↗
A numerical procedure to calculate the inviscid flow field about a space shuttle orbiter traveling at a supersonic/hypersonic velocity
Finite difference method for calculating inviscid flow field around supersonic/hypersonic space shuttle
Grossman, B.↗
Finite difference calculation of the behavior of a discontinuous signal near a caustic
Finite difference method for predicting sonic boom overpressure signature near caustic
Krupp, J. A.↗
Modified thermal analyzer digital computer program (TAP)
Computer program for solving n-dimensional transient or steady state heat flow problems by creating electrical analogy of problem and solving by finite difference method
Knittle, D. E.↗
Nonsimilar solutions for laminar film condensation of liquid metals
Liquid metals vapor drag and electromagnetic fields effects on laminar film condensation, using finite difference method
Denny, V. E.↗
Calculation of relaxing turbulent boundary layers downstream of tangential slot injection
Turbulent boundary layers calculation downstream of compressible relaxing slot injection flows, using finite difference method based on eddy viscosity model
Bushnell, D. M.↗
Dynamic buckling of shallow arches
Symmetric and asymmetric dynamic buckling of shallow elastic arches under uniform loads, using nonlinear finite difference method
Barton, F. W.↗
A Numerical Study of Displacement Body and Curvature Effects on Incompressible and Compressible Laminar Boundary Layers
This technique has been applied to study such effects on incompressible flow around cylinders at moderate to low Reynolds numbers and for compression ramps at hypersonic Mach numbers by employing a finite difference method to obtain numerical solutions. The results indicate that the technique can be applied successfully in both regimes and does predict the correct trend in regions of large curvature and displacement body effects. It was concluded that curvature corrections should only be attempted in cases where all displacement effects can be fully accounted for.
Wornom, S. F.↗
Flow field predictions for a slab delta wing at incidence
Theoretical results are presented for the structure of the hypersonic flow field of a blunt slab delta wing at moderately high angle of attack. Special attention is devoted to the interaction between the boundary layer and the inviscid entropy layer. The results are compared with experimental data. The three-dimensional inviscid flow is computed numerically by a marching finite difference method. Attention is concentrated on the windward side of the delta wing, where detailed comparisons are made with the data for shock shape and surface pressure distributions. Surface streamlines are generated, and used in the boundary layer analysis. The three-dimensional laminar boundary layer is computed numerically using a specially-developed technique based on small cross-flow in streamline coordinates. In the rear sections of the wing the boundary layer decreases drastically in the spanwise direction, so that it is still submerged in the entropy layer at the centerline, but surpasses it near the leading edge. Predicted heat transfer distributions are compared with experimental data.
Conti, R. J.↗