EXPERIMENTAL INVESTIGATION OF TURBULENT HEAT TRANSFER IN BOUNDARY LAYER OF SUPERSONIC HIGH-TEMPERATURE AIR FLOW ON FLAT PLATE IN SHOCK TUBE

Author(s):  
V. K. Shikov ◽  
E. V. Gurentsov ◽  
E. B. Eigenson
1960 ◽  
Vol 82 (4) ◽  
pp. 341-348 ◽  
Author(s):  
W. C. Reynolds ◽  
W. M. Kays ◽  
S. J. Kline

The results of an extensive experimental investigation of heat transfer to a turbulent incompressible boundary layer from a nonisothermal flat plate are summarized. Data presented extend the range of low-Mach-number confirmation of the von Karman analogy to Reynolds numbers of 4 × 106 for an isothermal plate. Data for a step wall-temperature distribution confirm experimentally the preferable expression for this important superposition kernel case. Data from a variety of other examples confirm the use of the superposition theories to predict heat transfer from nonisothermal surfaces.


2020 ◽  
Vol 2020 (0) ◽  
pp. 0125
Author(s):  
Hirofumi HATTORI ◽  
Keita KANO ◽  
Haruka TADANO ◽  
Tomoya HOURA ◽  
Masato TAGAWA

1973 ◽  
Vol 95 (4) ◽  
pp. 319-325 ◽  
Author(s):  
D. A. Nealy

Based on a simple enthalpy thickness approach, results are presented for laminar and turbulent heat transfer to a partially porous, nonisothermal flat plate. The model employed accounts for thermodynamic coupling between the boundary layer and porous wall heat transfer problems, and is expanded to include consideration of axial heat conduction along the wall. The results indicate that partial injection can be expected to produce a highly nonisothermal surface, which in turn causes the external Stanton number distribution to differ markedly from that predicted previously for assumed isothermal wall conditions. The boundary layer prediction technique is shown to be in reasonably good agreement with recent analytical and experimental results reported in the literature.


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