Aerodynamic Coefficient Predictions for a Projectile Configuration at Transonic Speeds

摘要

This report describes a computational study applied to a M549 projectile configuration. The objective was to apply previously developed Navier-Stokes computational techniques to the M549 shape, compare the results with available experimental data and evaluate the current computational capability. All computations and comparisons are for the transonic flight regime. The projectile flow fields, including the recirculatory base flow regions, were computed using thin-layer Navier-Stokes codes. Increased grid resolution and reduced computational time were achieved by using a vectorized code on a Cray 1S with one million words. Additional results were obtained using the same code on a two million word Cray. Aerodynamic coefficients have been determined from the computed flow fields and are compared to experimental data. The results for the static coefficients show good agreement with the data while the dynamic coefficients such as Magnus moment and roll damping need to be improved.