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Convective Heat Transfer on Flat Plate at Very High Temperature and Pressure Gradient PUBLIC ACCESS

[+] Author Affiliations
A. C. F. Pedrosa

Brasilian Air Force, Sao Jose Dos Campos, SP, Brasil

H. T. Nagamatsu

Rensselaer Polytechnic Institute, Troy, NY

Paper No. 83-GT-113, pp. V004T09A015; 10 pages
doi:10.1115/83-GT-113
From:
  • ASME 1983 International Gas Turbine Conference and Exhibit
  • Volume 4: Heat Transfer; Electric Power
  • Phoenix, Arizona, USA, March 27–31, 1983
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7954-2
  • Copyright © 1983 by ASME

abstract

This paper describes heat transfer measurements on flat plates for various free-stream temperatures, pressure gradients, Reynolds numbers and Mach numbers anticipated in advanced gas turbines. A shock tube generated the high temperature and pressure air flow, and a variable geometry test section was used to produce inlet flow Mach number of 0.11 and accelerate the flow over the plate to sonic velocity. Thin platinum film heat gages recorded the local surface heat flux for laminar, transition, and turbulent boundary layers. The free-stream temperatures varied from 630°R (350°K) to 4700°R (2611°K) for a Tw/Tr,g temperature ratio of 0.82 to 0.12 and Mach numbers from 0.11 to 1.90. The Reynolds number based on the model length was varied from 8.8 × 102 to 5 × 106. The experimental heat flux data were correlated with the laminar and turbulent theories and the transition phenomenon was examined.

Copyright © 1983 by ASME
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