Experimental Stanton number results are presented for the turbulent boundary layer on rough-wall flat plates with both constant wall temperature and constant wall heat flux boundary conditions. The experiments were performed with air in a boundary-layer wind tunnel with a maximum x-Reynolds number of 10,000,000. Two rough surfaces were used#x2014;one an otherwise smooth aluminum plate roughened with hemispheres spaced 4 diameters apart and the other the same but with the elements spaced 2 diameters apart. The data are compared with each other and with results from a smooth surface tested in the same experimental facility. It is found that, when considered as the ratio of constant heat flux Stanton number to constant wall temperature Stanton number, the data for all three surfaces collapse to the same curve as the Reynolds number increases.
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