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Liu, C.-H.

Publications and source records attributed to Liu, C.-H..

8 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1986

Implicit hybrid schemes for the flux-difference split, three-dimensional Navier-Stokes equations

Implicit hybrid algorithms employing symmetric planar Gauss-Seidel (SPGS) relaxation and either block-tridiagonally structured coefficient matrices (AF-SPGS) or block-triangular coefficient matrices (LU-SPGS) are derived to solve the flux-difference-split Navier-Stokes equations for three-dimensional incompressible flow in an upwind scheme. The physical basis of the approach is discussed, and results for problems involving vortex flow around a thin delta wing at Reynolds numbers 900,000 and 10,000 are presented graphically. It is found that AF-SPGS converges faster on vector computers which depend on long vector lengths to achieve optimum performance, whereas LU-SPGS is preferable on sequentially operating machines and vector computers using shorter vector lengths.

Hartwich, P.-M.↗
NASA NTRS1976

Numerical evaluation of the jet noise source distribution from far-field cross correlations

This paper contains the development of techniques to determine the relationship between the unknown source correlation function to the correlation of scattered amplitudes in a jet. This study has application to the determination of forward motion effects. The technique has been developed and tested on a model jet of high subsonic flow. Numerical solution was obtained by solving the Fredholm integral equation of the first kind. Interpretation of the apparent source distribution and its application to flight testing are provided.

Maestrello, L.↗
NASA NTRS1976

Entry into outer planet environments. I - The radiating shock layer with coupled ablation for carbon and silica

Fully coupled solutions of shock layer equations for the stagnation region are obtained, comprising a set of converged benchmark flowfield solutions for silica and carbon heat shields entering modeled atmospheres of Saturn and Uranus. Model atmospheres and entry trajectories providing significant radiative heating to the entry probes so that the heating environment and effects of mass addition on the heating environment are clearly defined are emphasized. Results referable to the carbon heat shield are questioned because of the high (sublimation) wall temperature assumed and the relatively low shock layer temperature.

Liu, C.-H.↗