Abstract
A technique is presented for solving the in viscid, chemically reacting, hypersonic flowfield over axisymmetric blunt bodies. The Euler equations are solved using a fully implicit, flux vector splitting, finite-difference scheme. An approximate factorization scheme is also used in order to improve computational efficiency. Finite-rate chemical reaction calculations are decoupled from the gas dynamic equations in the current analysis. Complex blunt body shapes, including highly indented nose geometries, are analyzed for Mach numbers from 2 to 18.
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