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An embedded grid formulation applied to delta wings
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Krist, Sherrie L. Thomas, James L. |
| Copyright Year | 1989 |
| Description | An embedded grid algorithm for the Euler and/or Navier-Stokes equations is developed and applied to delta wings at high angles of attack in low speed flow. The Navier-Stokes code is an implicit, finite volume algorithm, using flux difference splitting for the convective and pressure terms and central differencing for the viscous and heat transfer terms. Calculations are compared with detailed experimental results over an angle of attack range up to and beyond the maximum lift coefficient, corresponding to vortex breakdown at the trailing edge, for a delta wing nominally of unit aspect ratio. The results indicate that the overall flowfield, including surface pressures, surface streamlines, and vortex trajectories, can be simulated accurately with the global grid version of the present algorithm. However, comparison of computed velocities and vorticity with experimentally measured off-body values at an angle of attack of 20.5 deg indicates the core region is substantially more diffuse in the computations than that measured with either a five-hole probe or a laser velocimeter. Embedded grids, used to improve the numerical discretization in the core region, are formulated within the framework of the implicit, upwind-biased multi-grid algorithm. Structured levels of local nested refinements are made. Three-dimensional results for both Euler and Navier-Stokes calculations are shown, with up to 3 levels of embedded refinement. The embedding procedure was effective in eliminating a crossflow secondary separation produced in the Euler solutions on coarse grids. |
| File Size | 408739 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19910001578 |
| Archival Resource Key | ark:/13960/t21c6wc69 |
| Language | English |
| Publisher Date | 1989-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Computational Fluid Dynamics Aerodynamic Coefficients Vortex Breakdown Flux Difference Splitting Computer Programs Navier-stokes Equation Algorithms Three Dimensional Flow Finite Difference Theory Delta Wings Flow Distribution Flux Vector Splitting Computational Grids Angle of Attack Heat Transfer Cross Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
