The growing interest in Scramjets for achieving sustained hypersonic flight has given rise to numerous computational models to obtain solutions as close as possible to experimental data, assisting with making the design process of modern Scramjet’s with different propellants and cavity designs less costly. However, Scramjet engines pose significant challenges for computational modelling due to the need of accounting for large- and small-scale turbulences but also solving turbulence chemistry interactions in compressible flow regimes. A promising approach has been through using high-fidelity turbulence-combustion models which greatly assist with capturing detailed chemistry, account for small scale turbulence and the complex flow regimes found in these engines. With the Scalar Dissipation Rate having a direct effect on the Reaction Progress Variable, this paper expands on the prior 4-Dimensional Tabulated Conditional Moment Closure (TCMC) model by adding a fifth dimension as the Scalar Dissipation Rate into the TCMC model. Here, the US3D hypersonic CFD code is combined with the 5-Dimensional TCMC turbulent combustion model using a detailed kinetic mechanism to predict Scramjet unstart. Computational results are compared against the HIFiRE-2 flight conditions in the HIFiRE Direct Connect Rig (HDCR) experimental data providing promising results with reasonable runtimes.