Khalid A. Juhany, Mahmood Khalid and Amjad Ali Pasha
DOI Number XXX-YYY-ZZZ
Conference Number HiSST-2022-439
During a heat transfer study past blunt axisymmetric bodies and other tangent-cone and Gasjet models
equipped with forwarding flow facilities, the cylindrical shock exhibited atypical instability toward
complete and comprehensive numerical resolution. Such undesired flow behavior is not present in reallife flows when such blunt axisymmetric models are launched in the atmosphere or tested in wind
tunnels. The well-behaved shock in real life is observed as soon as the high Mach number flow impacts
the model. The region before and immediately after the shock is fraught with high and low Mach
numbers and extreme pressure conditions with invariable onset of disturbances traveling normal to the
shock. It is suspected that such complex physical changes in a small region give rise to numerical errors
that tend to compound in time and lead to shock instabilities, particularly close to the axis of symmetry.
It had been postulated that various second and fourth-order fluxes provisioned to capture shocks in
Euler flows may give rise to such instabilities, which it was reasoned would be removed through the
use of viscous flows computed using the Navier Stokes equation. The present studies were conducted
on a range of axisymmetric models. It was observed, however, that this carbuncle was most dominantly
demonstrated on a Gasjet model, which effectively is a blunt, leading model with a sharply truncated
front face.