In the present work, a numerical investigation is carried out for the laminar supersonic flow past a square obstacle mounted on a flat plate. The results are computed for Mach number ranging from 1.5 to 3.5 in steps of 0.5 and the free stream Reynolds number of 104. A new scheme for the computation of compressible flow has been introduced. The scheme is an explicit two step predictor-corrector scheme which is second order accurate in time and first order accurate in space. The flow characteristics around the surface mounted square obstacle are extensively studied. The spatial pattern comprises of a weak leading edge boundary layer shock, a strong oblique shock in front of the obstacle, separated regions in front and back of the obstacle, an expansion fan and a recompression shock. As the Mach number is increased from 1.5 to 2.0, the length of separated region and the location of strong oblique shock wave in front of the obstacle change significantly. Further increase in Mach number bas only a slight effect on front separation length and the location of oblique shock wave. The base separated length is also significantly affected by an increase in Mach number. Important design parameters such as surface pressure, coefficient of skin friction, wall Stanton number, peak wall pressure, drag coefficient and lengths of separated regions are explicitly reported as a function of the Mach number.
|Original language||English (US)|
|Number of pages||10|
|Journal||Collection of Technical Papers - AIAA Applied Aerodynamics Conference|
|State||Published - Jan 1 2005|
|Event||23rd AIAA Applied Aerodynamics Conference - Toronto, ON, Canada|
Duration: Jun 6 2005 → Jun 9 2005
ASJC Scopus subject areas