Accession Number : ADA135711

Title :   Solution Procedures for Accurate Numerical Simulations of Flow in Turbomachinery Cascades.

Descriptive Note : Interim rept.,


Personal Author(s) : Thompkins,W T , Jr ; Tong,S S ; Bush,R H ; Usab,W J , Jr ; Norton,R J G

PDF Url : ADA135711

Report Date : Jan 1983

Pagination or Media Count : 17

Abstract : For several years the authors have been evaluating and developing numerical simulation schemes for compressible, two dimensional inviscid or viscous flows in turbomachinery cascades. Numerical schemes considered, all originally classified as time-marching schemes, include: 1) implicit approximate factorization schemes; 2) explicit schemes due to MacCormack; 3) explicit central difference schemes; and 4) the mult-grid scheme of Ni. As we develop these schemes we came to believe that the accuracy of computational results is relatively insensitive to the numerical algorithm chosen but highly sensitive to implementation details such as boundary conditions, consistent flux balancing, grid resolution and numerical smoothing. To illustrate our viewpoint, we present an examination of the relationship between a flux balancing interpretation of the control volume conservation laws and various finite difference formulations and comparisons of the performance of these schemes on three test problems: Ni's bump in a channel, a supersonic nozzle, and flow in a supercritical compressor cascade.

Descriptors :   *Cascades(Fluid dynamics), *Computerized simulation, *Numerical methods and procedures, Turbomachinery, Compressible flow, Supercritical flow, Algorithms, Mathematical prediction, Sensitivity, Data processing, Problem solving, Boundaries, Grids(Coordinates), Resolution, Stagnation pressure, Finite difference theory, Operators(Mathematics), Inviscid flow, Solutions(General), Steady state, Cascade structures, Internal, Supersonic nozzles, Nozzle gas flow

Subject Categories : Theoretical Mathematics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE