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Aerodynamic Prediction for Supersonic Canard-Tail Missiles

M. F. E. Dillenius

Abstract

LRCDM2 computer program developed to calculate pressure distribution at points on surfaces of complete supersonic missile. Missile comprises up to two finned sections attached to axisymmetric body of circular cross section. Includes effects of vortex shedding due to forebody and forward fins, providing more accurate rolling moments. LRCDM2 written in FORTRAN IV.

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Key concepts: Supersonic speed, Aerodynamics, Missile, Aerospace engineering, Rotational symmetry, Mechanics, Fortran, Engineering