Inviscid and Viscous Solutions for Airfoil/Cascade Flows Using a Locally Implicit Algorithm on Adaptive Meshes PUBLIC ACCESS

[+] Author Affiliations
C. J. Hwang, J. L. Liu

National Cheng Kung University, Tainan, Taiwan, R.O.C.

Paper No. 90-GT-262, pp. V001T01A091; 8 pages
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME


A numerical solution procedure, which includes a locally implicit finite volume scheme and an adaptive mesh generation technique, has been developed to study airfoil and cascade flows. The Euler/Navier-Stokes, continuity and energy equations, in conjunction with Baldwin-Lomax model for turbulent flow, are solved in cartesian coordinate system. To simulate physical phenomena efficiently and correctly, a mixed type of mesh, the unstructured triangular cell for the inviscid region and structured quadrilateral cell for the viscous, boundary layer and wake regions, is introduced in this work. The inviscid flows passing through a channel with circular arc bump, and the laminar flows over a flat plate with/without shock interaction are investigated to confirm the accuracy, convergence and solution-adaptibility of the numerical approach. To further prove the reliability and capability of the present solution procedure, the inviscid/viscous results for flows over the NACA 0012 airfoil, NACA 65-(12)10 compressor and one advanced transonic turbine cascade are compared to the numerical and experimental data given in related papers and reports.

Copyright © 1990 by ASME
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