This paper experimentally investigated the rotational effects on heat transfer in a two-pass rectangular channel (AR=1:4), which is applicable to the channel near the leading edge of the gas turbine blade. The test channel has radially outward flow in the first passage through a re-directed sharp bend entrance and radially inward flow in the second passage after a 180° sharp turn. In the first passage, rotation effects on heat transfer are reduced by the re-directed sharp bend entrance. In the second passage, under rotating conditions, both leading and trailing surfaces experienced heat transfer enhancements above the stationary case. Rotation greatly increased heat transfer enhancement in the tip region up to a maximum Nu ratio (Nu/Nus) of 2.4. The objective of the current study is to perform an extended parameter study of the low rotation number (0-0.3) and low buoyancy parameter (0-0.2) achieved previously. By varying the Reynolds numbers (10000-40000) and the rotational speeds (0-400 rpm), the increased range of the rotation number and buoyancy parameter reached in this study are 0-0.67 and 0-1.9, respectively. The higher rotation number and buoyancy parameter have been correlated very well to predict the rotational heat transfer in the two-pass, 1:4 aspect ratio flow channel.