Some Modifications to, and Operational Experiences With, the Two-Dimensional, Finite-Difference, Boundary-Layer Code, STAN5 PUBLIC ACCESS

[+] Author Affiliations
R. E. Gaugler

NASA-Lewis Research Center, Cleveland, OH

Paper No. 81-GT-89, pp. V003T09A007; 5 pages
  • ASME 1981 International Gas Turbine Conference and Products Show
  • Volume 3: Heat Transfer; Electric Power
  • Houston, Texas, USA, March 9–12, 1981
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7963-4
  • Copyright © 1981 by ASME


The two-dimensional, finite-difference boundary-layer code, STAN5, is the primary tool used at the NASA-Lewis Research Center for predicting turbine blade gas-side heat-transfer coefficients. A number of modifications have been made to the program to enhance its usefulness for these calculations. Experience in using STAN5 has identified some problems in the program that can be treated through program input, without modifying the program. These include the presence of a small separation bubble near the leading edge, and the effect of full-coverage film cooling on transition to turbulence. Some of the techniques used to treat these problems are described.

Copyright © 1981 by ASME
Topics: Boundary layers
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