Time Accurate Computation of Unsteady Inlet Flows with a Dynamic Flow Adaptive Mesh.
Final rept. 15 Mar 1992-30 Jun 1994
NORTH CAROLINA STATE UNIV AT RALEIGH DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
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Research has been performed to obtain very accurate dynamic simulations of supersonic inlet unstart using CFD codes and a dynamic solution adaptive mesh algorithm developed at NCSU. The codes use Runge-Kutta time differencing and Advective Upwind Split Method spatial differencing in finite volume form. Other changes have been incorporated to improve the time accuracy when the computational mesh is dynamically adapted. Solutions have been obtained and animated for unstart of generic 2-D mixed compressions and fully supersonic inlets. Analysis of results revealed that laminar viscous flow unstart occurs by a separationoblique shock mechanism rather than movement of a normal shock. Turbulent flow simulations reveal that initial shock motion occurs initially but then reverts to the separationoblique shock mechanisms. 3-D steady and unsteady simulations are presented and conclusions drawn concerning the role of separation in inlet unstart. Computational fluid dynamics, Dynamic adaptive mesh, Mixed compression inlet unstart, Unsteady flow.
- Computer Programming and Software
- Fluid Mechanics