Abstract
The ZEUS program, which solves Euler's equations by spatial marching, is applied to conventional missiles characterized by circular cross-sectional bodies, canard control surfaces, and a cruciform tail. ZEUS incorporates a multiple-zone gridding technique and a second-order extension of Godunov's method. The Godunov method is an upwind scheme based on the Riemann problem for steady supersonic flow and cast in a control volume form. Second-order accuracy is obtained by computing local slopes and adding a predictor step. The scheme fits the bow shock and captures imbedded shocks. The ZEUS code is applied to two canard-controlled missiles with cruciform tails to predict longitudinal and lateral-directional (e.g., induced rolling moment) aerodynamic characteristics.
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