Many aerospace applications require parallel implicit solution strategies and software. We consider the use of two computational tools, PETSc and ADIFOR, to implement a Newton-Krylov-Schwarz method with pseudo-transient continuation for a particular application, namely, a steady-state, fully implicit, three-dimensional compressible Euler model of ow over an M6 wing. We describe how automatic di...

An analytical model is developed for the startup transient of asymmetrical flat-plate and diskshaped heat pipes. The model solves the proper transient heat conduction equations for the heat pipe wall and liquid-wick regions. A quasi-steady state, pseudo three-dimensional approximation is used for the vapor transi’ent behavior. The heat transfer within the wall and liquid-wick regions is coupled...

In this study, the hyperbolic method is adopted to explore flow field states of incompressible in a four-sided lid-driven square cavity. particular, we focus on bifurcation obtained at critical Reynolds number . method, diffusive term transformed into one by introducing diffusion flux term, which solution an additional equation. A classical Riemann-like solver with finite-volume discretization ...

We review and extend to the compressible regime an earlier parallelization of an implicit incompressible unstructured Euler code KKS98], and solve for ow over an M6 wing in subsonic, transonic, and supersonic regimes. While the parallelization philosophy of the compressible case is identical to the incompressible, we focus here on the nonlinear and linear convergence rates, which vary in diiere...

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