Understanding the behavior and design of total temperature probes used in gas turbine engines and other hot high-speed flows remains an active area of work, given the demands set by extreme operating conditions and ever-decreasing sensor size requirements. Where probe strut/mount cooling is necessary for probe survivability, conduction effects can be significant. The most effective mitigation of conduction errors results from convective heat transfer over the sensor. The goal of this paper is to provide a deeper understanding of the flow physics responsible for establishing the convective heat transfer on the sensor surface of vented-shield total temperature probes. This was accomplished by using high-fidelity computational fluid dynamics with conjugate heat transfer to examine the details of the aerodynamic environment establishing the heat transfer on the sensor surface. Probe geometric parameters varied and include the axial vent location, sensor diameter, and shield outer diameter. These parameters are cast into a set of nondimensional parameters that are used to build a set of correlations for local Reynolds numbers over regions of the sensor and Stanton number correlations for film coefficients. These film coefficients can be directly used in the new and existing low-order analytic thermal conduction probe performance models presented here and in the literature.