The presence of an adverse pressure gradient, shock/shock interaction and shock wave/boundary layer interaction often induces flow separation around bodies. However, the effect of dissociated flow on separated flow charact eristics, especially at hypersonic speeds, is still not clear, and considerable differences are observed between experiments and numerical simulations. In this investigation, the unsteady separated flow features around double cones are visualized in the Shock Wave Research Center (SWRC) free -piston driven shock tunnel at a nominal Mach Number of 6.99 using multiple optical techniques. The time resolved shock structure oscillations in the flow field around double cones (first cone, semi-apex angle = 25°; second cone, semi-apex angles=50°, 65°, 68° and 70°) have been visualized using a high-speed image converter camera (IMACON) at a nominal stagnation enthalpy of 4.8 MJ/kg. In addition, flow visualization studies around the double cone is also carried out using Schlieren and double exposure holographic interferometry in order to precisely locate the separation point and measure the separation length. The presence of a triple shock structure in front of the second cone and a non-linear unsteady shock structure oscillation in the flow field are the significant results from visualization studies on the 25°/65°, 25°/68°and 25°/70° double cones. On the other hand, the flow field around 25°/50° is relatively steady and Type V shock/shock interactio n is observed. Illustrative numerical simulation studies are carried out by solving N -S equations to complement the experiments. The simulated flow features around a double cone agree well qualitatively with experiments.
- Separated hypersonic flow
- Shock tunnel
ASJC Scopus subject areas
- Condensed Matter Physics
- Electrical and Electronic Engineering