Boundary layer transition prediction plays a vital role in the design of hypersonic vehicles as it decides the aero-thermodynamic characteristics such as drag and heat transfer rate. In this work, the Menter’s one equation (γ) transition model designed for low-speed flows is modified to predict the transition onset location and transition length for hypersonic flows. The capability of Menter’s model (2015) model in predicting transition in hypersonic flows and its sensitivity to the freestream eddy viscosity ratio is studied using an in-house 2D finite volume solver. An empirical correlation for the inlet viscosity ratio, along with the compressibility correction added in the modified model, predicts the transition onset correctly in high-speed flows.