Estimation of Aerodynamic Heating on Scramjet Inlets and Validation With Measurements

Aerodynamic heating levels on a typical inlet configuration of a scramjet engine are estimated using both standard design correlations and numerical flow simulations. The stagnation point heat flux is estimated using the Fay and Riddell formula. Aerodynamic heating over the inclined ramps is estimated using Van Driest method. Numerical flow simulations are carried out using a Reynolds averaged Navier-Stokes (RANS) solver coupled with energy equations and the Shear Stress Transport (SST) k-omega turbulence model. The aerodynamic heat flux estimates are validated with in-house measurements in a shock tunnel and for a scramjet flight experiment in the Mach number range 1.59 to 7.92. The emergence of a good agreement between them confirms the appropriateness of design correlations for heat flux estimation in scramjet inlets. The choice of simplification and appropriateness of design correlations to complex geometries demand critical assessment. Numerical flow simulations capture flow features and enable the identification of potential augmented heating zones, which will be critical for long-duration scramjet missions.

Automated summary

In this study, both standard design correlations and numerical flow simulations were used to estimate the aerodynamic heating levels on a typical inlet configuration of a scramjet engine. The results were validated with in-house measurements and flight experiments, confirming the appropriateness of the design correlations. The numerical simulations also identified potential augmented heating zones, which are critical for long-duration scramjet missions.