Adaptive Algorithm for Aircraft Configuration in Turbulent Flow
Abstract
The flow around aircraft configurations has been simulated. A code for numerical simulation and study of 3-D aircraft flowfields has been developed. The code consists of a hybrid scheme which solves the Navier-Stokes equations within the viscous regions around the aircraft while the simple Euler system is solved everywhere else. Efficient resolution of local flow physics such as shear layers,shock waves and vortices is achieved by a specially developed adaptive grid algorithm. The method employs division and/or deletion of grid cells, as well as redistribution of points in order to resolve local flow features more accurately and efficiently. A hybrid grid consisting of prisms and tetrahedra grid-cells is employed. The first type is appropriate for the viscous regions, while the second type is suitable for the inviscid regions. A grid generator of prisms around an F-16-type aircraft was developed. Flow visualization is greatly enhanced with a developed computer graphics code. Navier-Stokes numerical scheme, Euler numerical scheme, Adaptive grid, F-16 aircraft grid generation, Computer graphics, Aircraft flow simulations.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 25, 1992
- Accession Number
- ADA266188
Entities
People
- John Kallinderis
Organizations
- University of Texas at Austin