The most important problem in any spacecraft re-entry mission is the analysis of aerothermodynamics of re-entryconditions. One of the most commonly used shapes is the hemispherical cylindrical blunt body concept. Theaerothermodynamics of a hemispherical-cylindrical blunt body with a flow through duct is investigated numericallywith a commercially available Computational Fluid Dynamics software package Ansys Fluent 14.0. The constantarea circular duct starts at the nose of the axisymmetric model continues through the axis of the model and opens inthe atmosphere at the base of the model. With the blunt body at zero degrees angle of attack the presence ofstagnation point is eliminated. The effect of absence of the front stagnation point on the peak heat fluxes, total heattransfer rates and the overall drag is investigated in this paper. The projected cylindrical diameter of the re-entryvehicle is 40 mm and total length of the vehicle is 100 mm. The diameter of the axial duct is varied from 2 mm to 12mm. The free stream conditions used in the simulation are that of a typical point in the low lift ballistic re-entrytrajectory at an altitude of 30 km and a Mach number of 7.0. Thermally perfect gas model for air is assumed withoutany chemical reaction and model walls are assumed to be isothermal with a temperature of 500 K. This paperdiscusses the simulation results and projects recommended parameters.
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