Turbulent transition in hypersonic boundary layer is numerically investigated with a focus on effects of artificial dissipation in the computation. The artificial dissipation should be carefully controlled by adequate shock sensor for stable and accurate simulation of high-speed flows. In this study, the original shock sensor of the current flow solver, which is widely used in shock capturing methods, is modified to reduce the numerical dissipation in the transitional boundary layer. The current study indicates that well-controlled artificial dissipation allow major instabilities to grow properly and turbulent flow to be better resolved in hypersonic boundary layer flow.