Accession Number : ADP005136

Title :   Transonic Navier-Stokes Wing Solution Using a Zonal Approach. Part 2. High Angle-of-Attack Simulation,

Corporate Author : NATIONAL AERONUATICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER

Personal Author(s) : Chaderjian,Neal M.

Report Date : NOV 1986

Pagination or Media Count : 9

Abstract : A computer code is under development whereby the thin layer Reynolds averaged Navier Stokes equations are to be applied to realistic fighter-aircraft configurations. This transonic Navier Stokes code (TNS) utilizes a zonal approach in order to threat complex geometries and satisfy in-core computer memory constraints. The zonal approach has been applied to isolated wing geometries in order to facilitate code development. Part 1 of this paper addresses the TNS finite difference algorithm, zonal methodology, and code validation with experimental data. Part 2 of this paper addresses some numerical issues such as code robustness, efficiency, and accuracy at high angles of attack. Special free stream preserving metrics proved an effective way to great H-mesh singularities over a large range of severe flow conditions, including strong leading-edge flow gradients, massive shock induced separation, and stall. Furthermore, lift and drag coefficients have been computed for a wing up through sub L max. Numerical oil flow patterns and particle trajectories are presented both for subcritical and transonic flow. These flow simulations are rich with complex separated flow physics and demonstrate the efficiency and robustness of the zonal approach.

Descriptors :   *WINGS, *NAVIER STOKES EQUATIONS, *TRANSONIC CHARACTERISTICS, *COMPUTER PROGRAMMING, ANGLE OF ATTACK, REYNOLDS NUMBER, SUPERCRITICAL FLOW, FLOW VISUALIZATION, SHOCK, FLOW SEPARATION, GRIDS(COORDINATES)

Distribution Statement : APPROVED FOR PUBLIC RELEASE