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Transonic navier-stokes wing solution using a zonal approach. part 1: solution methodology and code validation
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Flores, J. Gundy, K. |
| Copyright Year | 1986 |
| Description | A fast diagonalized Beam-Warming algorithm is coupled with a zonal approach to solve the three-dimensional Euler/Navier-Stokes equations. The computer code, called Transonic Navier-Stokes (TNS), uses a total of four zones for wing configurations (or can be extended to complete aircraft configurations by adding zones). In the inner blocks near the wing surface, the thin-layer Navier-Stokes equations are solved, while in the outer two blocks the Euler equations are solved. The diagonal algorithm yields a speedup of as much as a factor of 40 over the original algorithm/zonal method code. The TNS code, in addition, has the capability to model wind tunnel walls. Transonic viscous solutions are obtained on a 150,000-point mesh for a NACA 0012 wing. A three-order-of-magnitude drop in the L2-norm of the residual requires approximately 500 iterations, which takes about 45 min of CPU time on a Cray-XMP processor. Simulations are also conducted for a different geometrical wing called WING C. All cases show good agreement with experimental data. |
| File Size | 767288 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19860020293 |
| Archival Resource Key | ark:/13960/t95769h8t |
| Language | English |
| Publisher Date | 1986-04-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Navier-stokes Equation Transonic Flow Wings Algorithms Aerodynamic Configurations Proving Problem Solving Computerized Simulation Wind Tunnel Walls Cray Computers Computer Programs Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
