| 1. |
- Boelens, O. J., et al.
(författare)
-
Description of the F-16XL geometry and computational grids used in CAWAPI
- 2007
-
Ingår i: Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting. - 1563478900 - 9781563478901 ; , s. 5866-5878
-
Konferensbidrag (refereegranskat)abstract
- The objective of the Cranked-Arrow Wing Aerodynamics Project International (CAWAPI) was to allow a comprehensive validation of Computational Fluid Dynamics methods against the CAWAP flight database. A major part of this work involved the generation of high-quality computational grids. Prior to the grid generation an IGES file containing the air tight geometry of the F-16XL aircraft was generated by a cooperation of some of the CAWAPI partners. Based on this geometry description both structured and unstructured grids have been generated. The baseline structured (multi-block) grid (and a family of derived grids) has been generated by the National Aerospace Laboratory NLR. The baseline all-tetrahedral and hybrid unstructured grids were generated at NASA Langley Research Center and the U.S. Air Force Academy, respectively. To provide more geometrical resolution, additional unstructured grids were generated at EADS-MAS, the UTSimCenter, and Boeing Phantom Works. All the grids generated within the framework of CAWAPI will be discussed.
|
|
| 2. |
- Görtz, Stefan, et al.
(författare)
-
Steady and unsteady CFD analysis of the F-16XL using the unstructured edge code
- 2007
-
Ingår i: Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting. - Reston, Virigina : American Institute of Aeronautics and Astronautics. - 1563478900 - 9781563478901 ; , s. 8258-8287
-
Konferensbidrag (refereegranskat)abstract
- Steady and unsteady viscous simulations of a full-scale, semi-span and full-span model of the F-16XL-1 aircraft at seven different flight Reynolds/Mach number combinations have been performed with an unstructured CFD code. The steady-state simulations are with several turbulence models of different complexity. Detached-Eddy Simulation (DES) has been used to compute the unsteady flow. The computed results are compared with public domain flight-test data. Very good agreement is demonstrated for surface pressure distribution, local skin friction and boundary velocity profiles. The different turbulence models performed almost equally well, except the Spalart-Allmaras model, which failed to predict the flow qualitatively and quantitatively. The Differential Reynolds Stress Model (DRSM) outperformed all other models when it comes to local span-wise skin friction. DES was superior over RANS modeling at the highest angle of attack, where the flow over the outer wing is separated and partly unsteady.
|
|
