Abstract
Aerodynamic coefficients of baseline missile noses and deformed missile noses at Mach 5 and 7 were calculated and compared using three kinds of approaches: 1) a density-based solver for CFD, 2) Newtonian theory, and 3) modified Newtonian theory. A blunt-cone shape was used as a baseline missile nose, and a deformed missile nose was generated by adapting the ablation model of a missile in the hypersonic region. The difference between the aerodynamics coefficients obtained from CFD and those obtained from the two theories was decreased as the Mach number increased. In terms of aerodynamic coefficient changes with the deformation of missile noses, the changes in drag and lift coefficients were similar for all three methods, but the changes in pitching moment coefficients were significant between CFD and the two theories.
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