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by Computational Aerothermodynamics, Brian R. Hollis, Brian R. Hollis, John N. Perkins, John N. Perkins, Kn Knudsen Number
ftp://ftp.kari.re.kr/NASA/larc/96/NASA-aiaa-96-1867.ps.Z
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Abstract:
Numerical solutions for hypersonic flows of carbon-dioxide and air around a 70-deg sphere-cone have been computed using an axisymmetric non-equilibrium Navier-Stokes solver. Freestream flow conditions for these computations were equivalent to those obtained in an experimental blunt-body heat-transfer study conducted in a high-enthalpy, hypervelocity expansion tube. Comparisons have been made between the computed and measured surface heat-transfer rates on the forebody and afterbody of the sphere-cone and on the sting which supported the test model. Computed forebody heating rates were within the estimated experimental uncertainties of ��10 % on the forebody and ��15 % in the wake except for within the recirculating flow region of the wake. NOMENCLATURE h enthalpy (J/kg)
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