Simulations of the HyShot-II (scramjet) model using high-resolution methods

This paper describes the application of a Finite Volume Godunov method to hypersonic ows with thermally perfect gas equation of state. The HyShot-II scramjet project has been used for this purpose. The HyShot-II conguration was tested in the High Enthalpy Shock Tunnel Goettingen (HEG) of the German Aerospace Center, DLR, and a Computational Fluid Dynamics (CFD) analysis was presented by Karl et al 10 using unstructured and Hybrid grids. The LES approach used in this paper employs a new fth-order accurate method in space with modied variable extrapolation on a structured grid at a ow of Mach 7.4 and altitude of 27 km. Two dimensional CFD analysis is presented on the complete geometry of the Hyshot-II scramjet and separately on the combustion chamber at fuel-o conditions using air as thermally perfect gas as a precursor to the future three dimensional studies. Two test cases for high Mach number thermally perfect gas ow, normal and oblique shocks, are also presented and the results are compared with NASA TPG (Thermally Perfect Gas) code results.

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