An Investigation was made at a Mach number of 3.12 to determine the effects of heat transfer on boundary-layer transition. Data were ob-tained for a cone cylinder and a parabolic-nosed cylinder at Reynoldsnnumbers up to 12×10° based on body length. The results show that cool-ing the cone-cylinder model to a wall-to-free-stream static-temperature ratio of approximately 1.4 increased the transition Reynolds number from a value of about 2.O106 at equilibrium to 10.6×10 . For temperature ratios less than 1.4, the boundary-layer flow was laminar over the entire model. The rapid increase of transition Reynolds number with small reduc¬tions in temperature ratio near 1.4 indicated that temperature ratios slightly lover may result in a laminar boundary layer for very high Reyn¬olds numbers. For the parabolic-nosed body, the transition Reynolds num¬ber was about twice that of the cone-cylinder model over the temperature range Investigated.
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