Abstract
For high aerodynamic drag and safe returning of capsule on the earth, to protect astronaut from radiation, the blunt shape reentry capsule is required. The flow fields over the blunt shaped reentry capsule are numerically obtained by the steady state, axisymmetric, compressible Navier–Stokes k-Ԑ turbulence model for free stream mach numbers are in the range of 2 and 4. Employing a finite volume approach which reduces the governing equations to semi-discretized ordinary differential equations. The numerical simulation is carried out on a structural grid. The flow field features around reentry capsule, such as bow shock, sonic line, expansion are obtained. A good agreement is found between the computationally calculated value of aerodynamic drag co-efficient blunt shape reentry capsule with the theoretical value. The effects of geometrical parameters, blunt shapes have been numerically investigated for various reentry configurations which will be useful for forming the strong shock wave in supersonic flow, as a result there is a increases in aerodynamic drag during landing of the vehicle.
Users
Please
log in to take part in the discussion (add own reviews or comments).